8 20 8242 https://digitalprojects.uah.edu/files/original/20/10399/Skyrwritermay1669_121310160610.pdf 076c90a2744af488938110e4b4ace376 Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context Skyrwritermay1669_121310160610.pdf spc_stnv_000805 Title A name given to the resource "All systems 'go' for liftoff of Apollo 10." Description An account of the resource News article detailing that the final preparations for the lift-off of the Apollo rocket have been completed. Creator An entity primarily responsible for making the resource Elliott, J. S. North American Rockwell Corporation Date A point or period of time associated with an event in the lifecycle of the resource 1969-05-16 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn project Aerospace industries Periodicals Type The nature or genre of the resource Text News Articles Source A related resource from which the described resource is derived Saturn V Collection Box 31, Folder 34 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000800_000824 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. http://libarchstor.uah.edu:8081/repositories/2/archival_objects/18117 https://digitalprojects.uah.edu/files/original/76/3311/loc_burw_-105.pdf 3d384ee284760a803ffe6b84815ade28 Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context Burwell Family Collection Title A name given to the resource Burwell Family Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/145" target="_blank" rel="noreferrer noopener">View the Burwell Family Collection finding aid in ArchivesSpace</a> Description An account of the resource <a href="http://libarchstor2.uah.edu/digitalcollections/items/show/3332" target="_blank" rel="noreferrer noopener">View Edwin D. Burwell's World War II service timeline, 1943-1944</a> <a href="http://libarchstor2.uah.edu/digitalcollections/items/show/3333" target="_blank" rel="noreferrer noopener">View Edwin D. Burwell's World War II service timeline, 1944-1945</a> Provenance A statement of any changes in ownership and custody of the resource since its creation that are significant for its authenticity, integrity, and interpretation. The statement may include a description of any changes successive custodians made to the resource. Materials donated and digitized by Dudley Burwell Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context loc_burw_000105 Title A name given to the resource "Allotment Discontinuance-Notice Upon Discharge or Release from Active Duty ". Creator An entity primarily responsible for making the resource Goldsmith, Jack Date A point or period of time associated with an event in the lifecycle of the resource 2/18/1946 Temporal Coverage Temporal characteristics of the resource. 1940-1941 Subject The topic of the resource Burwell, Edwin D., Jr. United States. Army Type The nature or genre of the resource Forms (Documents) Text Source A related resource from which the described resource is derived Burwell Family Collection University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource loc_burw_2021_02 https://digitalprojects.uah.edu/files/original/20/10434/scan0017rev_080107122437.jpg 714043e292e924b02f314ce1b1b8be86 Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context scan0017rev_080107122437.jpg spc_stnv_000790 Title A name given to the resource "Alloy designation" Table. Description An account of the resource 8 x 10 inch black and white photograph that displays a table of two elements and their molecular makeup. Table includes the alloy of LA-141 and LAZ-933. Creator An entity primarily responsible for making the resource George C. Marshall Space Flight Center. Propulsion & Vehicle Engineering Laboratory.Metallurgical Analysis Section. Materials Division, Metallic Materials Branch. Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn project Apollo project Liquid propellant rockets--Materials Space vehicles--Materials Alloys Spacecraft construction materials Type The nature or genre of the resource Still Image Photographs Source A related resource from which the described resource is derived Saturn V Collection University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Is Part Of A related resource in which the described resource is physically or logically included. Is referenced by: Materials in space exploration.; Is part of: Envelope - Photos Accompanied C. E. Cataldo paper "Materials in space exploration". Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000775_000799 https://digitalprojects.uah.edu/files/original/20/1143/spc_stnv_000059.pdf beba84b6e41e32c88a0b78d7553b40ee PDF Text Text :;x, Douglas Paper 3172 SATURN H:STORY DGC~.JMENT Univcisit-y of Alcbens Re-nrlrch institute History of Science & Technology G r o q Date ---------- Doc. No. -------- ALTITUDE SIMULATION I N SATURN SIV STAGE TESTING Prepared By: D . D . HOFFERTH Branch Chief Field Development Engineering Sacramento Test Center Sacramento, California E. L. WILSON Branch Chief Space Propulsion Branch Missile & Space Systems Division Huntington Beach, California A . L. POLANSKY Design Engineer Space Propulsion Branch Sacramento ~ e s Center t Sacramento, California Presented To: Society of Automotive Engineers DDUGLAS /M/SS/LE &: SPACE SYSTEMS D/V/S/UN / �ABSTRACT Altitude Simulation i n Saturn SIV Stage Testing The Douglas Aircraft Company has been invoived i n testing the Saturn SIV stage at the Sacramento Test Center for the past two years. The propulsion system for the SIV stage consists of six (6) Pratt & Whitney Aircraft Company rocket engines 0 which are designed specifically for high altitude start and operation. During static firing tests of this engine a t sea level, a steam jet ejector in combination with a diffuser, are used to simulate altitude conditions, The intent of this paper i s to examine the performance of this altitude simulation system, and to discuss problems encountered i n making i t operational. �The Douglas Aircraft Company has been involved i n testing the Saturn S I V stage a t the Sacramento Test Center for the past two years. The SIV i s an upper stage of the National Aeronautics and Space Administration's Saturn Space Vehicle. A later version of the Saturn Space Vehicle i s programmed to launch an Apollo to the moon. The propulsion system for the SIV stage consists o f six (6) Pratt 8, Whitney Aircraft Company RLIOA-3 rocket engines capable of generating a total of 90,000 pounds thrust a t as titude (Figure 1). These engines were designed specifically for high altitude start and operation and, therefore, require an altitude simulation system to permit sea level static testing. The normal starting altitude of the Pratt & Whitney RLlOA-3 engine, when used as part of the SIV stage, i s approximately 240,000 feet, where the expected absolute pressure i s 0.17 psia. I t i s not required that this low a pressure be obtained for sea level testing, however, The engine requires sufficient pressure drop between the liquid oxygen pump inlet and the combustion chamber to attain a pre-start flow o f liquid oxygen. This flow must be sufficient to cool the pump so that stall free acceleration and mainstage operation can be achieved. The time interval required, as w e l l as the quality and quantity of liquid oxygen required, had to be established during static testing. Even more basic, however, i s the requirement that the high expansion ratio (40: 1) thrust chamber bell be operated without flow separation. If the engine were operated a t sea level back pressures, separation would occur, , w i t h attendant structural and performance degradation. The engine bell construction �The Douglas Aircraft Company has been involved i n testing the Saturn SIV stage at the Sacramento Test Center for the past two years. The SIV i s an upper stage of the National Aeronautics and Space Administration's Saturn Space Vehicle. A later version of the Saturn Space Vehicle i s programmed to launch an Apollo to the moon. The propulsion system for the SIV stage consists of six (6) Pratt & Whitney Aircraft Company RLIOA-3 rocket engines capable of generating a total of 90,000 pounds thrust at altitude (Figure 1). These engines were designed specifically for high altitude start and operation and, therefore, require an altitude simulation system to permit sea level static testing. The normal starting altitude of the Pratt & Whitney RLlOA-3 engine, when used as part of the SIV stage, i s approximately 4240,000 feet, where the expected absolute pressure i s 0.17 psia. It i s not required that this low a pressure be obtained for sea level testing, however. The engine requires sufficIant pressure drop between the liquid oxygen pump inlet and the combustion chamber to attain a pre-start flow of liquid oxygen. This flow must be sufficient to cool the pump so that stall free acceleration and mainstage operation can be achieved. The time interval required, as well as the quality and quantity of liquid oxygen required, had to be established during static testing. Even more basic, however, i s the requirement that the high expansion ratio (40:l) thrust chamber bell be operated without flow separation. If the engine were operated at sea level back pressures, separation would occur, , with attendant structural and performance degradation. The engine bell construction �was intended for altitude operation and thus not designed to withstand the high loads which would be encountered i n sea level operation. The total altitude simulation system u t i l i z e d i n the SIV stage static testing (1) the diffusers, (2) the eiectors, (3) the i s comprised of four elements: accumulators, and (4) the steam boilers and 'feed water system (Figure 2). The diffusers are attached to each of the six engines w i t h a flexible seal, and are closed a t the opposite end by blow-off doors. In this configuration they serve as a vacuum chamber to provide low ambient pressures (less than 0.9 psis) i n the forty-five (45) second period up to and including engine ignition. By controlling the engine exhaust gas flow through internal geometry, the diffusers also sustain the required absolute pressure a t the engine bell e x i t after the engine start transient. The diffusers are approximately thirty-five (35) feet long, and are of double w a l l construction to provide for water cooling. The wal I s are fabricated from low carbon steel and are spaced one-fourth inch apart to accommodate a cooling water flow rate of approximately 3100 gallons per minute per diffuser. Each diffuser i s connected to a two stage steam jet ejector system w i t h a thirty.(30) inch vacuum line. A pneumatically operated butterfly valve i s installed i n this vacuum line to permit isolation of the eiectors from the diffusers. The i n i t i a l purpose of this isolation was twofold: (1) to prevent hot gases from the diffuser being sucked through the eiectors just after engine ignition, and (2) to prevent aspiration of a i r through the ejector and into the lower end of the diffuser during normal engine operation, where after-burning would cause high �temperatures and resultant damage to the diffusers. ... These butterfly valves were also found to be of value in the sequencing of ejector operation with respect to the diffuser during the initiation of vacuum pumping. Each stage of the two stage ejector i s thirty (30) feet long, and they are assembled together i n a vertical array on the front of the test stand (Figure 3). The first stage suction chamber i s at the level of the diffuser vacuum line. Steam reaches the second stage ejector without intervening valves between them and the constant pressure steam regulators. The first stage steam lines were provided with intervening three-inch valves to permit delaying the entrance of steam into the first stage ejectors until the second stage had established a partial vacuum throughout the system. I t was learned early i n testing of the altitude system, however, that this delay was not necessary inasmuch as no significant change i n vacuum pull-down characteristics were encountered with simultaneous admission of steam to both ejector stages. Mani- folding for delivery of steam to both stages of the ejectors i s supplied through . an eighteen (18) inch steam line from the constant pressure regulators i n the accumulator area. Two thirty thousand (30,000) gallon capacity steam accumulators serve as storage vessels for the steam energy used to power the ejectors. These vessels are half-filled with water, and when charged, hold heat i n this water a t 406'~. he upper half of each accumulator contains steam a t 406'~ and 250 psig pressure. To insure optimum performance of the eiectors, motive steam i s supplied from the accumulators a t a constant pressure. his 'is accomplished by the use of constant �pressure regulators (one for each accumulator), which maintain 135 psia at the ejector nozzles. The regulators are of the twelve (12) inch, 90' angle valve type, and are commanded open and closed by the automatic SIV stage firing sequence. The actual opening travel of the regulating valve i s controlled by high pressure water from the accumulators. This controlling water i s regulated as a function of the pressure i n the eighteen (18) inch steam line. The opening travel of the poppet i n the constant pressure regulators then increases as the accumulator pressure falls off during a test run. A boiler of 250 BHP capacity i s used to produce 8625 pounds per hour of dry and saturated steam a t 250 psig for charging the steam accumulators. ' The process of charging the accumulators requires approximately twelve (12) hours. The "packageu boiler i s o i l fired, and i s automatically actuated with boiler steam pressure. The normal supporting systems for operation of a steam boiler are part of this complex area, which includes the feedwater system, deaemtor, blow down tank, and o i l storage tank. The design specifications for the steam supply system and ejectors of the altitude simulation system were established as a function of the Pratt & Whitney RLIOA-3 engine.chilldown flow rates during the period prior to engine ignition. The internal convergent-divergent geometry of the diffusers was established using the parameters of engine combustion products flow during firing operation to assure a sustained pressure of 3.0 psia or less at the engine bell exit. The Pratt & Whitney RLlOA-3 engine utilizes liquid oxygen and liquid hydrogen as propellants. Since both of these propellants have very low boiling �temperatures (-297' and -423O~, respectively), each pump must be chilled to essentially its respective liquid boiling point to assure that at engine ignition liquid w i l l be present at the pump inlet and not gas, since gas would cause pump cavitation. To accomplish adequate chilldown of' the liquid hydrogen pump a t sea level requires forty-five seconds of time, during which gaseous hydrogen i s 'dumped into a stand vent system, and carried off to a burn stack. During the last ten (10) seconds of this forty-five (45) second period, the liquid oxygen pump i s simultaneously being chilled down, and dumping approximately 2.0 pounds per second of first gaseous and then as chilldown proceeds, liquid oxygen into each diffuser. These gases must be carried out'bf each diffuser while continuously maintaining a pressure of 0.9 psia or less. The low pressure i n the diffusers during chilldown i s required to provide the proper pressure drop between the engine pump inlet and the engine combustion chamber or diffuser to assure the chilldown propellant flow rates. Operation of the altitude simulation system i n conjunction with the Pratt &,Whitney engine starting sequence was of such critical nature that control of the system was integrated into an automatic engine firing logic. As i s shown on Figure 4, the base for the timing of logic events was established with time T=O occuring at engine start command. A t T-60 seconds or fifteen (15) seconds prior to initiation of the firing logic, the manually switched sequence of starting three (3) electric motor-driven water pumps and opening of the deflector plate water: valve i s started. This timing assures full water flow through the cooling water jacket of the diffusers, as well as full water flow for deflector plate �cooling by engine start command. The automatic engine f i r i n g logic i s initiated a t the beginning of LH chilldown which i s forty-five (45) seconds 2 prior to engine ignition, or T-45 seconds. Simultaneous w i t h LH2 chilldown initiation, both the constant pressure regula toss and the first stage ejector steam valves are opened to begin the vacuum pumping action w i t h the diffuser butterfly valves closed. Ten (10) seconds later, a t T-35 seconds, the diffuser butterfly valves are opened, and the diffusers are evacuated to approximately 0.5 psia by pumping action from the operating ejectors. To provide feedback information to the automatic engine firing logic that the altitude simulation system i s functioning properly, specifically that the differserapressure i s a t or below 2 . 5 psia, pressure switches set to pick up a t 2.5 psia are installed on each diffuser. The picked-up talkback i s required from a l l six of the diffuser pressure switches by T-10 seconds to enable the logic signal commanding the start of the liquid oxygen pump chilldown. I f these talkbacks are not a l l received, a hold i s automatically imposed i n the logic. The d i f f i c u l t y must then be isolated and corrected before a recycle of the sequence can be performed. At T-0 seconds the logic signal for engine ignition i s given, and the first stage ejector steam valves are closed. After successful engine start i s achieved a t approximately T+2.4 seconds, as indicated by proper signals from each of the engines, the altitude simulation system i s automatically shut down by simultaneously closing the constant pressure regulators, and the diffuser butterfly valves. steam jet ejector system no longer operating, a pressure of less than With the 1.0 psia (3.0 psia maximum allowable) i s sustained a t the engine bell e x i t until engine cutoff, by the pressure physics of engine exhaust gas flow controlled by internal diffuser geometry �The actual data for diffuser operation during the acceptance firing of the f i f t h Saturn stage, the SIV-5 Vehicle, at Sacramento (Figure 5) shows typical performance values. As can be seen, approximately five (5) seconds after the butterfly valves were opened than - by T-30 seconds, a pressure of less 1.0 psia had been achieved i n each diffuser. This pressure was held constant until engine ignition, a t which point the diffuser pressure began to increase as the engines proceeded through their normal start transient and engine combustion chamber pressure increased. The pressure increase continued until T+2.0 seconds, when i t changed slope sharply, and caused the diffuser blow-off doors to be carried The pressure returned immediately then to less then 1 .O psia, and was rut- away. tained a t this value until engine cutoff occurred at T+477.5 seconds. With engine cutoff, the pressure i n each of the diffusers returned to ambient within one (1) second. Having discussed i n general terms the hardware elements of the altitude simulation system, and having reviewed typical performance data of the system as gathered during Saturn SIV-5 Vehicle firing, i t i s appropriate that some of the problems encountered i n achieving the present level of performance be discussed. As i t was. stated earlier, constant pressure regulators were installed a t each accumulator, to provide steam a t 135 psia to the ejectors for optimum performance of the ejectors i n vacuum pumping. Since the total duration of the steam eiector system operation for each test was only f i f t y (50) seconds, severe dynamic demands were,imposed on the constant pressure regulating system. Because of the mass of the moving elements i n the twelve (12) inch, 90' globe valves, which were the regulating �devices i n the steam line, time restrictions had to be imposed on opening and closing speed. This mass also caused overshoot difficulties which would not have been a problem i n an "on the line" system which was the application for which these regulators were designed. To understand the specific difficulty and how i t was corrected i t i s necessary to examine the elements of the constant pressure regulating system (Figure 6). For simplicity only one system i s shown, although i t was duplicated for each accumulator. The constant pressure regulator was operated i n its opening cycle by a regulated, constant bleed, wafer system which sensed the pressure i n the eighteen (18) inch steam line as its controlling function. water was obtained from the bottom of the accumulator. The The force of water on the opening side of the constant pressure regulator actuating piston was counterbalanced by a controlled source of gaseous nitrogen. On command from the automatic engine firing logic, at T-45 seconds, for steam to be supplied to the ejectors, an electrical signal caused the shutoff valve i n the water regulating system to open. This permitted high pressure water to reach the opening side of the actuator on the constant pressure regulator, driving i t 'open, and a t the same time compressing the gaseous nitrogen on the upper side of the actuating piston. The pressure increase i n the eighteen (18) inch steam line was sensed and fed back to the water regulator which began to close down the water shutoff valve, and thence the water flow to the opening side of the actuator. Thus the constant pressure regulator reached that position which would supply steam to the ejectors a t 135 psia . �1 I n the original installation cooling coils were provided i n the water line to the water regulator to assure that high pressure water without entrapped steam would be available for motive force at the actuating piston of the constant pressure regulator. I t was quicltly discovered, however, that the change i n pressure a t the regulated water shutoff valve caused the water to flash to steam. This condition caused the \ constant pressure regulator to be driven f u l l cycle open to closed and back to open, and rendered the water regulating system ineffective i n establishing a constant steam pressure. To assure that cool water was always available to the regulating system, a one hundred (1 00) gal Ion water tank was added downstream .of the cooling coils. This f i x worked effectively and permitted additional testing of this system which established that the response of the constant pressure regulator to i n i t i a l overshoot was too slow. Specifically, the range of pressure during the overshoot was 180 psia to 200 psia, and the time from the open command signal until stable pressure was achieved was approximately sixty (6C) seconds. Since only forth-five (45) seconds of steam system operation were required, this system transient was unacceptable. The d i f f i c u l t y was f i n a l l y traced to excess volume i n the water regulating system, which caused excessive time for the water to be bled off and, therefore, slow response of the constant pressure regulator to the overshoot. When the volume of the water system was reduced by short coupling the elements of that system to the constant pressure regulator, this problem was solved and acceptable performance was .achieved. system i s shown i n Figure 7 A composite of typical data from the altitude simulation Note that the magnitude o f overshoot i s approximately �170 psia - not significantly changed from the 180 to 200 psia level - but that stable pressure regulation i n the eighteen (18) inch steam line i s achieved w i t h i n thirty (30) seconds of the open command. During the i n i t i a l static tests of the Saturn SIV Vehicle a t the Sacramento Test Center, an aluminum blow-off door was used as the closure on the diffusers. This door weighed approximately one-hundred and twenty (120) pounds, and was held i n place a t the lower end of the diffuser by four (4), four hundred (400) pound pull magnets. The blow-off doors remained i n place on the diffusers prior to engine start, and were then ejected from the diffusers at engine start as the chamber pressure increased. Because of the force w i t h which the doors were ejected, some damage was always sustained as they contacted w i t h the test stand flame deflector plate. Experience quickly established that the aluminum doors could usual l y be repaired for use a second time, but that repair beyond this point was not practical. The high usage rate of aluminum doors, and high i n i t i a l cost coupled w i t h the cost involved i n the repair operation, created the incentive for fabrication of fiberglass doors. Testing o f a blow-off door fabricated of fiberglass, quickly established clear advantages of this product over the one fabricated of aluminum: (1) the fiberglass door weighed less than one-half as much as the aluminum door (53 pounds compared to 120 pounds) and offered considerable advantage i n handling the doors for installation, and (2) fiberglass construction resulted i n doors which were flexible and liable enough to absorb impact w i t h sustaining damage. the flame deflector plate without The combination of light weight and f l e x i b i l i t y o f the fiber- glass doors was manifested i n l i t t l e damage being incurred by the doors w i t h �each use and established a high reuse factor. This reuse factor coupled w i t h lower i n i t i a l costs and lower repair cost, as compared w i t h the aluminum door, permitted a savings of several thousand dollars i n the Saturn SIV program. Before and during the early portions of the hot firing program, i t was found that some of the diffuser doors would occasionally blow off upon activation of the altitude simulation system. This w w l d result i n the i n a b i l i t y to draw a vacuum i n those diffusers affected and thereby cause an automatic cutoff. It was first thought that flame deflector plate water flow was washing the doors o f f and the operating sequence was changed to assure a t least partial vacuum prior to achieving f u l l deflector plate water flow. The persisted however, and several additional factors were evaluated. 4 I t was found that i n i t i a t i o n of steam flow i n the ejector generated a momentary but very slight overpressure i n the diffusers, which could contribute to door blow-off . By starting the steam blow-down w i t h butterfly valves closed, this surge was prevented from entering the lower ( ~ l e n u m )section of the diffusers immediately above the doors. The most direct cause of door loss was attributed to the accumulation o f water i n the steam supply lines. The i n i t i a l design incorporated preheat valves that permitted a small quantity of steam to bypass the constant pressure regulating valves for the purpose of conditioning the lines downstream. i t was intended that this would reduce condensation during the i n i t i a t i o n of steam flow t o the eiectors. Unfortunately, the preheat steam condensed into large accumulations of water, and i n i t i a l main steam flow carried this water to the ejectors w i t h attendant �water hammer loads i n the lines, ejectors, and diffusers. Preheat was eliminated - 9 . very early i n the test program, but the water "slugging" problem persisted, although i t was less severe. The entrained water would cause violent shock loads i n the ejectors as i t turned corners and eventually went through the elector nozzles, and these loads were transmitted to the diffuser through the connecting thirty (30) inch ducts with sufficient force to actually shake the doors off. The addition of drains to the system a t a l l low points, and particularly immediately upstream and downstream of the constant pressure regulating valves solved this problem. The condensation occurring during initial flow of steam into cold lines was less severe than anticipated. With the incorporation of procedures for draining water which had accumulated a t a l l low points i n the steam lines to the ejectors, and changing of the logic sequence to open the butterfly valves after steam flow was well established i n the eiectors, operation of the altitude simulation system became very re1iable. The double-walled diffuser construction, mentioned earlier, i s shown i n Figure 8. The inner wall i s one piece, 5/16 inch thick, extending from the engine exit to the plenum section (Section #8). The plenum i s separable from the rest of the diffuser and incorporates a section of water-cooled 30-inch vacuum line. Spacer rings of 1/4 inch square cross section are welded to the inner wall every six (6) inches. The rings are not'ched to permit some longitudinal equalization of water flow and to permit a i r and/or vapor to be vented. The outer'shell i s two pieces, each welded to one of the end flanges of the inner wall. A slip joint gland seal midway along the diffuser permits each half of the outer she1l to move freely i n the axial direction, thus preventing buckling �loads on the inner w a l l during the expansion caused by heat generated during a static firing. outer shell. Water i s introduced into the annvlus through holes i n the The i n l e t and outlet water manifolds are essentially identical, half-round sections of pipe covering the holes and having flanged connectors t o the test stand water distribution manifolds. Initially, no attempt a t controlling the vertical distribution of water flow was made. Water temperature was monitored a t one point i n the final discharge line from each diffuser, and a single diffuser was instrumented a t each water discharge point to establish a profile of temperature along the length of the diffuser. The first two static firings, of 10 and 14 seconds duration, were insufficient i n duration to establish a temperature profile a t the cooling water discharge ports. The third firing was aborted a t 28.5 seconds because of what was then considered an excessive water discharge temperature of 165'~. Although no physical damage occurred, orifices were instal led i n the outlet flanges of the upper sections of the diffuses tcs force more of the flow through the lower sections. The allowable water discharge temperature was raised from 1 6 5 ' ~ to 1 9 0 ' ~ and static firings of 62, 41, and 7 seconds were accomplished w i t h no overheat evidenced. The first f u l l duration 420 second firing, the seventh static firing, resulted i n extensive damage to the plenum section of the diffusers, even though the maximwm allowable water temperature was not exceeded. I t was determined that local boiling or trapped a i r near the water outlet o f the lower section of the diffusers restricted water flow sufficiently t o permit hot spots to develop to the point that the inner liner became plastic and bulged inward. Metal flow occurred a t the bulge i n each diffuser, and i n �one case was of sufficient magnitude to cause the bulge to rupture, The exit water manifolds were removed from each diffuser and additional holes drilled through the outer wall to reduce restriction to water flow. Vent holes to eliminate air traps at the upper end of each section were also added i n the outer wall. The orifices were changed i n a19 the outlet flanges i n an attempt to distribute water flow such that a constant tempemture rise would be obtafned across each diffuser section, The discharge water from the previously damaged lower section was diverted from the collection manifolds feeding the deflector plate, and used to cob1 the bellows section i n the 30 inch duct connecting the diffusers to the steam iniectors. The next full duration firing resulted I n a small bubble i n Section # 1 of Diffuser Number 2, and the respective outlet orifice was enlarged for a l l six (6) diffusers, Subsequent full dumtlon firing tests on both the battleship test vehicle, and four (4) fltght vehicles were performed with no further difficulties encountered i n cooling of the diffusers. The altitude simulation system described i n this paper has been used to accomplish some thirty-one (31) static firing tests. Each of these tests involved the functioning of a set of steam ejectors and diffusers for each of the six engines utilized on the Saturn SIV sta$e. In this sense, one hundred and eighty-six (186) operational cycles were accomplished i n simulating altitude conditions for an engine firing. While problems were encountered i n making the total a! titude simulation system functional, they were solved quickly a? the beginning of the staticatestingprogram. The performance of the system i n achieving the low pressures required, and i n achieving them with a high level of reliability has been we1l estdbl ished as very satisfactory. ����FIGURE 4 I I -7 -6 -5 -4 -3 -2 -1 I i i i i i i i i i i -30 -20 -10 -9 -8 I I 8 +l +2 +f +4 +S I I I I I I I I i I 1 I +s 4-7+8 +1+1@ 4-9+$O+t)+t) +@ i i i i i i i 1 i I 1 SATURN S-IV GROUND TEST START SEQUENCE i EXPANDED TIME SCALE (SECONDS) -60 -50-40 WATER VALVE OPEN DEFLECTOR WATER PUMPS 1-2-3 DEFLECTOR PLATE STATIC FIRING AUTO SEQUENCE 1ST STAGE STEAM EJECTORS ON 2ND STAGE STEAM UECTORS ON DIFFUSER PRESS. MONITOR SWITCHES ENABLED LH2 PRESTART VALVES OPEN LOX PRESTART VALVES OPEN ENGINE IGNITERS ON ENGINE START VALVES W E N ENGINE PRESSURE QK �5 SATURN SIV-5 ENGINE DIFFUSER OPERATION PRESSURE aLGUMVOiWS f CO)ISTAfdl i1STSTUXEJETOR VALVES OPEN �FIGURE 6 FROM PNEUMATIC VALVE REGULATOR SOLENOID VALVE HAND VALVE NCHECK VALVE - CONSTANT PRESSURE REGaBMTGq CONTROL SYSTEM WATER SHUTOFF & MWUUTING VALVE CONSTANT WATER ( & �PRESSURE-PSIA �DIFFUSER W A E R 8) � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000059 Title A name given to the resource "Altitude Simulation in Saturn SIV Space Testing." Description An account of the resource This paper was presented to the Society of Automotive Engineers. The abstract reads, "The Douglas Aircraft Company has been involved in testing the Saturn SIV stage at the Sacramento Test Center for the past two years. The propulsion system for the SIV stage consists of six (6) Pratt & Whitney Aircraft Company rocket engines which are designed specifically for high altitude start and operation. During static firing tests of this engine at sea level, a steam jet ejector in combination with a diffuser, are used to simulate altitude conditions. The intent of this paper is to examine the performance of this altitude simulation system, and to discuss problems encountered in making it operational." Creator An entity primarily responsible for making the resource Hofferth, D. D. Polansky, A. L. Wilson, E. L. Douglas Aircraft Company. Missile and Space Systems Division Date A point or period of time associated with an event in the lifecycle of the resource 1965-01-01 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn Project (U.S.) Saturn launch vehicles--Testing Saturn S-4 stage Altitude simulation Type The nature or genre of the resource Reports Text Source A related resource from which the described resource is derived Saturn V Collection Box 12, Folder 60 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000051_000074 https://digitalprojects.uah.edu/files/original/125/8517/r04c03-14.pdf 676c1cb82167ad218a7a5beff05f6589 Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context Series 04, Subseries C: Alabama History Title A name given to the resource Series 04, Subseries C: Alabama History Still Image A static visual representation. Examples include paintings, drawings, graphic designs, plans and maps. Recommended best practice is to assign the type Text to images of textual materials. Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context r04c03-14 Source A related resource from which the described resource is derived Series 4, Subseries C, Box 3, Folder 14 Title A name given to the resource "America's First Frontier Railroad" Paper by McCanless, George F. Jr Description An account of the resource Miscellaneous Alabama Relation A related resource r04c-211007 https://digitalprojects.uah.edu/files/original/20/1145/spc_stnv_000061.pdf 271b6a70fbb7b29e2196d2c74298e1b7 PDF Text Text I John F. Space Center N A T I O N A L A E R O N A U T I C S A N D SPACE A D M I N I S T R A T I O N KM HISTORY DOCUP ity of Aiabama Researcl QF Science 6 Technolc _ -LI-..-----D=N~.-------- - AMERICA'S SPACEPORT �"The story of man's achievement thrmgh30ut history has been the story of his victory over the forces of nature. In that continuing story, our generation has been given the opportunity to write the grandest chapter of them all. It i s on our schedule, in oar plm, and in our determination to put men 092 the moon before 2370." President Lyndon B. Johnson sept.n, 1966 �W E L-COME... , . ' .& . Welcome to the John F. Kennedy Space Center, NASA. This i s the major launch base from which manned and unmanned spacecraft explore the environment beyond the Earth's atmosphere, reaching out to the Moon, the Sun and the planets. Thousands of dedicated engineers, scientists, technicians and support personnel, members of an integrated GovernmentIndustry team, have created these facilities. The Center's superb launch team has achieved many "firsts" i n man's conquest of space. These accomplishments represent an important phase of the Nation's effort to achieve and maintain preeminence i n space research and exploration. I trust you w i l l share our pride i n the unique environment of the launch center and the historic work being carried on here. John F. Kurt H. Debus, Director Kennedy Space Center, NASA �MISSION John F. Kennedy Space Center i s the major NASA launch organization for manned and un: manned space missions. As the lead center within NASA for the development of launch philosophy, procedures, technology and facilities, Kennedy Space Center launches Apollo space vehicles; unmanned lunar, planetary and interplanetary spacecraft; and scientific, meteorological and communications satellites. The mission encompasses planning and directing: Preflight Preparations Vehicle Integration Test and Checkout of Launch Vehicles, Spacecraft and Foci liti es Coordination of Range Requirements Countdown and Launch Operations Supporting t h i s primary mission are a host of technical and administrative activities. These include design engineering; testing, assembly and checkout of launch vehicles and spacecraft; launch operations; and purchasing and contracting. The national Spaceport i s the site from which American astronauts w i l l be launched on lunar exploration missions before the end o f the decade. The A i r Force Eastern Test Range, part o f the Air Force Systems Command, operates and maintains the largest missile proving ground i n the free The Test world, one that spans 10,000 miles. Range's mission i s to provide launch f a c i l i t i e s and support services for launching missiles and spacecraft, and gather useful data from the flights. The Range supports NASA-sponsored launches for the peaceful exploration of space. �The National Aeronautics and Space Administration was established October 1, 1958. T h i s was 12 months after the launch o f Sputnik 1, the f i r s t man-made Earth satellite, and n i n e months after the launch o f Explorer 1, the f i r s t United States satellite. The maior focus o f NASA's launch operations has centered on Cape Kennedy, formerly Cape Canaveral, Florida. The antecedents of these a c t i v i t i e s date back to t h e years f o l l o w i n g World War II when the War Department selected the s i t e as a t e s t i n g area for longrange guided missiles. T h i s s p i t o f land i u t t i n g into the A t l a n t i c Ocean wos selected because o f the chain o f islands stretching southeastward t o Ascension Island which could accommodate tracking stations to measure the f l i g h t of research and development vehicles. The s i t e was formally approved J u l y 8, 1947. Soon afterward, Congress author i z e d the acquisition and construction o f the A t l a n t i c M i s s i l e Range, now the Eastern T e s t Range. A s a Department o f Defense facility, the range was assigned to the A i r Force for management. Subsequently, the range was extended t o the Indian Ocean, a distance o f more than 10,000 miles. The Army and Navy have a l s o u t i l i z e d the range f a c i l i t i e s i n the development o f rocket-powered weapons systems. As the NASA program got underway, the Cape became the headquarters of the Launch Operations Center, later renamed the John F. Kennedy Space Center, NASA. In late 1964, the Kennedy Space Center was relocated on adiacent Merr i t t Island. The s i t e occupies some Here, foci l i t i e s have 88,000 acres. been installed t o accommodate enormously powerful space vehicles t o carry man to the Moon and back, and to undertake even more challenging missions i n the vast reaches o f the universe. By noteworthy coincidence, the Spaceport has an unusual heritage. Numerous Indian burial mounds and middens (refuse piles) have been discovered on NASA property. Researchers have removed artifacts dating back to the time of Christ. Elsewhere, part i c u l a r l y along the beaches, traces have been found of early Spanish activity. Dr. Charles Fairbanks of the University of Florida has pointed out: 'This was one of the areas where Western c i v i l i z a t i o n came to the New World, and now it i s the area from which our c i v i l i z a t i o n w i l l go forth to other worlds." �LAUNCH VEHICLES T h e United States space program depends on the $ability o f scientists and engineers t o provide the means for propelling useful pay loads i n t o Earth orbit and into the farther reaches of space. For t h i s task, launch vehic l e s of varying sizes and capabilities are necessary. The f l i g h t path chosen for a payload determines what performance i s required of the particular launch vehicle. Obviously, it would be impractical to use our most powerful launch vehicle, the Saturn V, t o orbit a small, lightweight group o f s c i e n t i f i c satellites, or to r i s k failure of a mission by placing too much weight on a launch vehicle of any size. For these reasons, NASA has developed a family o f r e l i a b l e launch �vehicles of different sizes, shapes and capabilities. The objective has been to develop the smallest number of vehicles consistent with the f u l l scope of the space program. Launch vehicles employed for space missions i n the recent past evolved principally from basic military systems developed and tested during the previous decade. Technological exchange between military and scient i f i c projects continues to benefit the national space program. The f i r s t United States satellite was orbited by an Army-developed Jupiter-C missile. Delta, the workhorse of NASA's unmanned spacecraft program, employs components developed by the A i r Force and Navy. Modi- SATURN I fied Army/Air Force developed Redstone and Atlas boosters were utilized for the Mercury program, this country's i n i t i a l manned space flight effort. The Gemini launch vehicle was a modified Air Force Titan II booster. Centaur, the world's f i r s t space launch vehicle to be powered by liquid hydrogen fuel, and the highly successful Ranger and Mariner space probes were boosted into space by modified Air Force Atlas vehicles. The Saturn family of heavy launch vehicles, which was developed by NASA expressly for the peaceful exploration of space, evolved from technology acquired during the Army's early Redstone, Jupiter and Juno miss i l e development programs. A P O L L O / U P R A T E D SATURN �MANNED SPACE FLIGHT For thousands of years man has dreamed of the day when he would explore the vast universe that surrounds his tiny planet. This aspiration has stemmed from his fundamental thirst for knowledge and his readiness to accept the challenge of the unknown. When Orville Wright made the first powered flight in 1903 at a speed of 31 miles per hour, the significance of his achievement was barely recognized. Yet, in l i t t l e more than half a century following that historic event at Kitty Hawk, man' has succeeded i n orbiting the Earth at speeds measured in thousands of miles per hour. Now, he i s literally reaching for the Moon as the first stop on the way to exploration of the solar system and the infinite reaches of interstellar space beyond. The achievements in space since the first satellites were launched have paled to insignificance when compared with future proiects. Only i n the light of what he has already accomplished can man look ahead with the almost certain knowledge that he eventually w i l l realize his age-old dream of exploring the universe. Viewed in terms of time and distance, the challenge of space exploration seems insurmountable. Yet, a review of the technological accomplishments of the 20th century indicates that what appears as impossible i s merely difficult. The exploration of space i s following the pattern by which flight within the atmosphere was mastered. Each new development provides a platform from which to take the next step, and each step i s an increment of scientific knowledge and technological skill. ��MERCCJRY Project Mercury, the first of the manned space flight programs, was organized October 5, 1958, and successfully executed i n less than five years. The primary objectives of Proiect Mercury were: To place a manned spacecraft i n orbital flight around the Earth. To investigate man's performance capabilities and his abili t y to function in the environment of space. To recover, safely, both man and spacecraft. Project Mercury demonstrated that the high-gravity forces of launch and reentry, and weightlessness in orbit for as much as 34 hours, did not impair man's ability to control a spacecraft. I t proved that man not only augments the automated spacecraft controls, but also can conduct scientific observations and experiments. - Moreover, Project Mercury proved that man can respond to and record the unexpected, a faculty beyond the capability of a machine which can be programmed only to deal with what i s known or expected. In addition, the Mercury flights confirmed that man can consume food and beverages and perform other normal functions while i n a weightless environment. Finally, Mercury laid a sound foundation for the technology of manned space flight. The Mercury spacecraft, a one-man, bell-shaped vehicle, 9.5 feet high and 6 feet across at its reentry heat shield base, weighed approximately 4,000 pounds at liftoff and 2,400 pounds at recovery. The launch vehicle for the Mercury suborbital missions was a modified Redstone rocket generating 78,000 pounds of thrust at liftoff. A modified Atlas rocket whose three engines produced 367,000 pounds thrust was employed for Mercury orbital flights. Complexes 56 and 14 at Cape Kennedy were utilized for the Mercury missions. �GEMINI &mini was %he Lntermdiate step tawutd ~ h i c n r i n gB manpad lwsw land# ing, bridgina the afIigjhtexp4ilcnce k w e m tke S ~ W T - ~ Q ~ missions andhe lang durdflm mirsions of Apollo. Major obitctives achieved during the p r ~ r a m included d*mons+ration that man can perform effectively during extended periods i n spoce, both within and outside the p~oiectivaenviron.men+ of a spacecraft, development crf r m dezwus and doeking techniques, and parfelttan of controlled rsenTry and landing procedures. The Gemin i progrm provided fhe first American demonstratim of arbi tal rendezvous a skill which must be devdeped to land Amsriean exploxers on the Meon and is camduct the adwnced ventures of the future. The welaan Gemini spaeemafr was also a bll-shaped vehicle; however, it was almost twice as heavy, SQ perceht larger and contained 50 per- wmq - cccn? more valume than the Mercury saw&crafit. The tatsneh vehicle empleyed i n the C m i n i prepram was the modified Air Force Titan tl rocket which devdoped a thrust of 430,000 pounds at liftoff. The o v ~ ~ length l t af the Gmttni-Titan ll spa&@vehicle was 109 h t , Gemini flights wwe launched from Complex 19 at Cope Kennedyelr, The t a r p t vahicls fos thq Gemini r.(tndezvuur ond docking misrims was B d i f i e d Agena-D vehicle with (J fwwad moun~edtarget docking adapter, which provldedtb connecting point far mwting wjth the &mini srraaecrdt. The Agena-a, with a multiple restwt capability, had a rated thrust o f appmxim&aly 16,W pcrunds. it was' launched an an Atlas Standard Launch Vehicle which generates about 390,000 pounds of thrust. Gemini Aflas/Agena t a r p t vehiefrs had an avarall length of 104 fret. They were lounched from Complex 14 at Cape Kennedy. �r '. Tf sign- FJ,,F3Jh . \ ' .. �fir.-+.- Apollo i s the largest and most complex of the manned spoce flight programs. Its goal i s to land American astronauts on the Moon and return them safely to Earth. The astronauts w i l l travel to the Moon in the three-man Apollo spacecraft. Weighing 45 tons, the spacecraft consists of three sections - a command module, a service module and a lunar module. The command module may-be likened to the crew compartmentof a commercial jet airliner. It i s designed so that thrse men can eat, sleep and work in it without wearing pressure suits. Of the three modules, only the command module w i l l return to Earth. Thus, it i s constructed to withstand the tremendous deceleration forces and intense heating caused by reentry into the Earth's atmosphere, The service module contains supplies, fuel and a rocket engine so the astronauts can maneuver their craft into and out of lunar orbit and alter their course and speed in space. > l-. k 1 The lunar module i s designed to carry two men from lunar orbit to the Moon's surface for exploration and and then back into lunar orbit for rendezvous with the command and service modules. After the crew transfers back to the command module, the lunar module i s jettisoned and left in lunar orbit. Providingthe muscle for theApollo program i s the Saturn family of heavy launch vehicles. The first of these to be flight tested by the Kennedy Space Center was the Saturn I. Developing 1.5million pounds of thrust at liftoff, theSaturn I demonstrated the feasibility , .- . . = r d of clustered rocket boosters and qualified vehicle guidance and control systems. It also tested the structure and design of the Apollo command and service modules, physical compatibility of the launch vehicle and spacecraft and iettisoning of the Apollo launch escape system. Additionally, Saturn I vehicles orbited large Pegasus micrometeoroid detection satellites to monitor the frequency of micrometeoroids and to determine if they would be a hazard to manned space flights. Currently, uprated Saturn flight programs are underway at Kennedy Space Center. W i t h the greater power of the uprated Saturn, a l l three modules of the Apollo spacecraft are launched into Earth orbit. Initially, the flights are unmanned. Soon, uprated Saturn vehicles w i l l launch three astronauts on Earth orbital missions up to 14 days in duration. Lunar missions w i l l use the enormous power of the Saturn V launch vehicle. Together with the three modules of the Apollo spacecraft, the Saturn V stands 364 feet, weighs about 6 million pounds at launch and develops 7.5 million pounds of thrust at liftoff. Development of the Saturn vehicles i s the responsibility of the Marshall Space Flight Center, Huntsville, Alabama. The Manned Spacecraft Center, Houston, Texas, has responsi bility for Apollo spacecraft development, training of the flight crews and conducting the flight missions. Assembly, checkout and launch of the ApolloSaturn space vehicles are conducted at Cape Kennedy and at the Nation's Spaceport by Kennedy Space Center. �1 ;,I ' '. 5' - SATELLITES AND SPACE -. PROBES .-... �Unmanned spacecraft are making important contributions to man's knowledge ahout the world in which he lives and the universe around him. Much of this knowledge i s derived from the growing family of scientific satellites and space probes launched by Kennedy Space Center. Explorer satellites have mapped the Earth's magnetic field and have pioneered i n gaining new knowledge of the Earth's shape and mass distribution. Explorer I, this country's first satellitewhich was launched from Cape Kennedy on January 31,1958, discovered that the Earth was partially surrounded by a belt of deadly radiation, subsequent1y named the Van Allen Radiation Region. Other satellites have furnished information on micrometeoroids,temperatures in space, radiation and magnetic fields, upper atmospheric conditions, solar activity and other phenomena. Meteorological satellites have achieved the most significant advances in weather forecasting since the invention of the barometer over three centuries ago. T I ROS satellites, the first of a series of orbiting "weathermen," were launched from Cape Kennedy Complex 17 by Delta vehicles beginning i n April 1960. These satellites returned well over a million cloud:over photographs of the Earth's surrace. Starting in 1966, operational ueather satellites were launched for the Environmental Science Services Admini stration by Kennedy Space Center personnel. Placed into polar 3rbit from the Western Test Range in Ealiforn ia, these satellites photograph cloud cover and transmit pictures to weather stations akound the world. This type of fast, accurate weather reporting coupled with long-range weather prediction can be worth untold millions of dollars to agriculture, business and industry. Communications satellites such as Echo, Telstar, Relay, Syncom and Early Bird, launched on Delta vehicles trom Cape Kennedy's Complex 17, are shrinking the distances between continents, and are leading to better under- standing among the world's people. Exploration of the Moon's surface and environment by unmanned space probes i s essential to obtain data for manned lunar landings. This type of information i s also important i n yielding clues to the origin of the Moon, the solar system and perhaps even the universe. Rangers 7, 8 and 9 returned thousands of close-up pictures of the Moaj before smashing into the lunar surfac+: On June 2, 1966, the Surveyor I space& craft, the first of a series of instryk mented soft-landers, settled gently onto the lunar surface and transmitted thousands of detailed photographs ba* to Earth. Other Surveyor soft-landers are making detailed examinations of the Moon's physical phenomena and surface composition. These spacecraft are launched by Atladcentaur vehicles from Cape Kennedy Complex 36. Lunar Orbiter spacecraft, circling the Moon in low orbit, have photographed with amazing clarity wide areas of the lunar landscape. Launched from Complex 13 at Cape Kennedy, the Lunar Orbiter missions have provided significant data on potential landing sites for Apollo astronauts. Investigations of other planets of the solar system are conducted by unmanned Mariner spacecraft. On December 14, 1962, Mariner 2 became the first spacecraft to scan another planet at close range as i t passed within 21,600 miles of Venus. Mariner 4, after an eight-month iourney, passed . within 6,000 miles of Mars on July 14, 1965. Instrument observation of the plahet yielded invaluable clues to scientists seeking clues to the possibility of life on Mars. Mariner spacecraft are launched by Atlas/Agena vehicles from Cape Kennedy Complexes 12 and 13. Goddard Space Flight Center manages NASA's unmanned scientific,, meteorological and communications satellite programs. Unmanned lunar, planetary and interplanetary programs are managed by Jet Propulsion Laboratory. Launch operations for these programs are conducted by the Kennedy Space Center. �LAUNCH COMPLEX 39 Launch Complex 39, the nation's f i ~ s toperational spaceport, ranks as one of history's great engineering achievements. Developed and operated by the Kennedy Space Center, the immense facility is designed to accommodate the massive Apollo/Saturn V space vehicle which w i l l carry American astronauts to the Moon. Complex39 reflects a new approach to launch operations. In contrast to the launch facilities presently utilized at Cape Kennedy, Complex 39 permits a high launch rate, economy of operation . .. and superior flexibility. This new approach, known as the 'mobile concept," provides for assembly and checkout of the Apollo/Saturn V vehicle in the controlled environment of a building, i t s subsequent transfer to a distant launch siteand launch with a minimum of time on the launch ad. The maior components of Complex 39 include: the Vehicle Assembly Building, where the space vehicle i s assembled and tested; the Launch Control Center, which houses display, monitoring and control equipment for �checkout and launch operations; the Mobile Launcher, upon which the space vehicle i s erected for checkout, transfer and launch and which provides internal access to the vehicle and spacecraft during testing; the Transporter, which transfers the space vehicle and Mobile Launcher to the launch site; the Crawlerway, a specially prepared roadway over which the Transporter travels to deliver the Apollo/Saturn V to the launch site; the Mobile Service Structure, which provides external access to the vehicle and spacecraft at the launch site; and the launch site, from which the space vehicle i s launched on Earth orbital and lunar missions. The Vehicle Assembly Building provides a startling contrast to the low Merritt Island landscape. Covering 8 acres of ground, the Vehicle Assembly Building conslsts of two major working areas: a 525-foot-high high bay area and a 210-foot-high low bay area. The- high bay contains four vehicle assembly and checkout bays, each capable of accomrnodoting a fully ossembled, heavy-class space vehicle. The low bay contains eight preparation and p heck out cells for the upper stages of the SacturnV vehicle. Vehicle stages are shipped by barge from fabricatian centers to a turning basin near the Vehicle Assembly Bui lding, off-loaded onto special carriers and transported to the building. The first stage i s towed to the high bay area and erected on the Mobile Launcher. Four holddown-support arms on the Mobile Launcher platform secure the booster in place. Work are positioned around the booster for inspection and testing. Concurrently, upper stages of the Saturn V are delivered to the low bay cells, inspected, and tested. When testing of the individwal stages i s completed, the upper stages are prepared for mating and moved to the high bay area. A l l components of the space vehicle, including the Apollo spacecraft, ore assembled vertically in the high bay area. The fully assembled space vehicle then undergoes final integrated checkout and simulated flight tests. Located adjacent to the Vehicle Assembly Building and connected to the high bay area by an enclosed bridge i s the Launch Control Center. All phases of launch operations at Complex 39 are controlled from this four-story concrete structure. The first floor of the Launch Control Center contains offices, a dispensary and a cafeteria. The second floor is allocated to telemetry, measuring and checkout systems for use during stage and vehicle assembly in the Vehicle Assembly Building, and for launch operations at the launch site. Four firing rooms occupy the third floor one for each high bay in the Vehicle Assembly Building. These rooms contain control, monitoring and display equipmentreqwired fw automatic vehicle checkout and launch. Each firing room i s supported by a computer room, which is a key element in the automatic checkout and launch sequence. The Mobile Launcher, the key to launch operations at Cemplex 39, actuallyperforms a dual function. It serves as an assembly within the Vehicle Assembly Building and as a launch ~ l a t f o r mand umbilical tower at the launch site located several miles away. The Mobile Launcher i s a 446-foothigh structure with a base platform measuring 25 feet high, 160 feet long and 135 feet wide. I t weighs 10.6 million pounds. Whether in the Vehicle Assembly Building, at the launch site, - �or in its parking area, theM~bileLauncher ir positioned on six 22-foot-high steel pedestals. Nine swing arms extend from the Mobile Launcher's tower. The three astronauts wi ll enter the Apol lo spacecraftvia the top swing arm. These arms are dei~igrrrrdto swing rapidly away from the vehicle during launch, Besides carrying vital umbilical lines prapellant, pneumatic, electrical, data link to the space vehicle, the swing apms also permit a catwalk access to the vehicle during tfaa final ~ h a s eof countdown. The ApolloAaturn V i s p s i t i m e d on the Mobile Launcher and secured by f a r suppart and holddown arms. At the pad these arms hold the vehicla during thrust buildup of ths engines. A 45-square-foot spcning in the k s e plotform permits passage of engine exhausts at ignition. Three Mebile Launchers have been corrsttuctrd at Complex 39. A tracked vehicle hnewn as the Trclnsporfer moves thc 36-stsry Apol lo/ Saturn V space vehicle and Mobile Launcher horn the Vehicle Assembly Building to the launch site. Two Trans- - - are stutioned a t Camplex 39. "Ihe Transporter i s similar to ma- porters chines used in strip mining operations. Weighing app~aximately6 mi Illan ponds, it i s 131 feet long and 114 M w?&. Its height is adjustabls froa aQ to 26 feet. The vehicle moves on. h r J~ltlLletracked crawlers, e s h 10 %a& high and 40 feet long. Each shwe & ~ m l c r track weighs atrout a tat. ffrwa W Q $? shws on each h a c k B F F ~l ~ ~ t 1 1of 8 tracks on the c n t h A t a l s . Two main Civet d i m 1 engines provide 5,500 hnrsepwe-r. T* aher diesels gsnerah 2,t 30 h w ~ p ~ w e farr Ievk-ling, iackhg, rtew~tlsg, Il@ng, verrtiloting and sfsctrsnia syat%ns. Aurilimty plmimature pmvide power to the Mabila L W W RwG h~ carried by the Trurrhparter. Fn optaatian, the Jranspwter s l ips under the Mabile Lwncher while inside the Vehicle Assembly Building, Its 16 hydraulic i a ~ k s rulsctheMobila Launcher, with the spaee vehicle aboard, from support pdestals, The leaded Tranoporter then backs out of the Vehicle Assembly Building and transfers the 11.5-million-pound-load 3.5 mil& te the �launch site. The Transporter has a speed of 1 mile per hour when fwlly loaded and twice that when unloaded. It can negotiate curves of 500 feet mean radius. A leveling system provides the capability to maintain the entire load i n level position during *he transfer operation. The combined weight of the Transporter, the Mobile Launcher m d the Apollo/Saturn V exceeds 17 million ~ o u n d sa t the time of transfer from the Vehicle Assembly Building to the launch site. To accommodate fhis load, a specially constructed Crawlerway was prepared. The Crawlerway extends from the Vehicle Assembly Building to the launch site, and consists of twa 40foot-wide lanes separated by a SOfoot-wide median strip. The overall width of the roadway i s 130 feet or about equal to an eight-lane parkway. Unsuitable material was removed from the roadbed before beginning construction of the Crawlerway. The area than was compacted with hydraulic fill and selected material s, topped with crushed graded lirnerock, paved w ith asphalt, sealed and covered with gravel, forming a roadbed approximately 7 feet thick. From eight to twelve thousand pounds-pet-square-foot in surface prossures are exerted on the Crawlerway; this i s equivalent to a stress of 40 iet- liners landing at the same time on a runway. The Mobile Service Structure i s a 402-foot-high tower which weighs 12 million pounds. The structure contains five service platforms that provide circular access to the space vehicle for final servicing at the launch site. The two lower platforms can be adiusted up and down the vehicle, while the three upper platforms have a fixed elevation. Like the Mobile Launcher, the Mobile Service Structure i s transported to the launch site by the Transporter. I t is removed from the pad a few hours prior to launch and returned to its parking area. Two launch sites are located at Complex 39, three and one-half miles from the Vehicle Assembly Building. Each site i s an eight-sided polygon measuring 3,000 feet across. The maior elements of the launch iites include the launch pads; storage tanks for liquid oxygen, liquid hydrogen and RP-1 propellants; gas compressor facilities; and associated umbilical connection lines necessary for launching the space vehicle. The launch pad itself i s a reinforced concrete hardsite measuring 390 feet by 325 feet. Top elevation of the pad is 48 feet above sea level, sufficient distance for the rocket's engine nozzles to rest above a 700,000-pound flame deflector. �INDUSTRIAL AREA The lndustrial Area of the Kennedy Space Center i s located 5 miles south of Launch Complex 39. The area was planned so that a l l functions not required at the launch complexes could be grouped for ease of administration and efficient operations. Here, the administrators, scientists, engineers and technicians plan and accomplish many of the detailed operations associated with prelaunch testing and preparing space vehicles for a mission. The Headquarters building i s the admin istrative center for spaceport operations. Dr. Kurt H. Debus, Director of the Kennedy Space Center, and his immediate staff maintain offices on the top floors. Procurement, program management, legal and other support functions occupy lower floors. The largest structure i n the Industrial Area i s the Manned Spacecraft Operations building. This facility i s used for modification, assembly and nonhazardous checkout of Apollo spacecraft. It also provides astronaut quarters and medical facilities, spacecraft automatic testing stations and complete supporting laboratories. Following systems testing and Apollo service module static firing, Apol lo spacecraft are delivered t o this building for integrated systems testing. Here, individual spacecraft modules undergo acceptance testing and integrated systems and altitude chamber testing. Two 50-foot altitude chambers environmentally test Apol lo spacecraft in conditions simulating altitudes up to 250,000 feet. Space-suited astronauts participate i n these simulated flight tests. The Information Systems facility i s the hub of thespaceport's instrumentation and data processing operations. It provides instrumentation to receive, monitor, process, display and record information received from the space vehicle during test, launch and flight. The lndustrial Area contains special laboratories and testing facilities for the hazardous checkout operations associated with spacecraft pyrotechnic devices and toxic fluids. Among the other maior f a c i l i t i e s located i n the lndustrial Area are: �- Flight Crew Training Building this foci li t y provides an environment where astronauts and flight controllers under the direction of Manned Spacecraft Center personnel can practice for manned Apollo space missions. actual Apollo spacecratt and creates nearly complete realism for simulated missions. For about three weeks prior to a mission, astronauts go through makebelieve flights and cope with purposely contrived emergency situations. - - - L i f e Support Test this facility i s used for high-pressure testing and liquid oxygen supply testing of environmental control systems. FluidTestSupport this facility i s a single-story structure housing laboratories, shops and service areas to support the entire test area. Critical component lesting of spacecraft fluid test [systems are conducted i n the laboratories which maintain special clean-room conditions. Hypergolic Test this facility i s used to test and check out stabilization and attitude control systems, orbital maneuvering systems and reentry control systems for spacecraft. Hypergotic fluids utilized i n these systems are especially hazardous since they ignite upon contact with each other. Cryogenic Test this facility i s used for checking the cryogenic systems of spacecraft. Cryogenic fluids are supercooled. An example would be liquid hydrogen which must be maintained a t a temperature of 423 degrees below zero. Pyrotechnic Installation this ten-story-high facility i s used to install spacecraft pyrotechnic - - - - devices and to statically weigh and balance the spacecraft i n i t s mission configuration to determine its center of gravity. The facility i s also used for optical alignments of critical components of the guidance and navigation systems, as well as acceleration tests on dynamic fixtures. Ordnance Storage this facility provides remote, safe storage for solid fuel motors, pyrotechnic devices and aligned launch escape towers. RF Systems ~ e s t this facility i s used to adiust, test and check out spacecraft rendezvous apparatus and procedures in a simulated free space condition. Transmitting antenna height, elevation, squint and azimuth angles and transmitter frequency are remotely controlled from an operator's console. - - Additional support structures in the Industrial Area include cafeteria, warehouses, fire station, security offices, utilities and occupational health fac i l i ties. �CAPE KENNEDY FACILITIES Stretching northward along the Atlantic Ocean are the famous launch complexes of Cape Kennedy. The Cape i s managed by the U. S. Air Force for theDepartment of D e fense and designated as Station 1 of the Eastern Test Range which reaches 10,000 miles to the Indian Ocean. The U. S. Army, Navy and Air Force have used the Cape's f a c i l ities for missile development programs. Since the advent of the national space program in 1958, however, the area has also been u t i l i z e d by NASA as a launch s'ite for space vehicles. In the foreground are the two pads of Launch Complex 36 from which Surveyor spacecraft are launched toward the Moon. �Ten manned space missions were launched from Complex 19 during the highly successfu! Gemini program. Here, the Gemini 12 vehicle, the final flight i n the program, i s readied for launch. At the right i s the erector which i s employed i n servicing the space vehicle. Prior to launch, the erector i s lowered t o the ground. The umbilical tower on the left carries electri call communications and propellant lines to the rocket. lt remains attached t o the vehicle until liftoff. - A t Launch Complex 34, one of two Saturn launch sites on Cape Kennedy, the 300-foottall service structure encloses an uprated Saturn launch vehicle. Unlike the erector used at Complex 19, this structure moves back from the launch ready vehicle on rails. At nearby Complex 37, another Saturn launch site, a similar structure serves two launch pads that are connected by rails. From these sites, astronauts w i l l be launched on Earth orbital missions i n - . the three man Apollo spacecraft. - 1 , ,.This view of Launch Complex 37 shows the service structure in an open position with an rated Saturn launch, vehicle on the pad. To afford launch crews access to the rocket, the service structure closer around the Saturn. The platforms, which can be seen i n the photograph, provide work levels at various stages of the configuration. This unmanned Saturn, AS- 203, was successfully launched July 5, 1W6. The mission was an orbital flight t o examine the effects of weightlessness on the liquid hydrogen fuel of the second stage. For this reason, i t was equipped with a nose cone instead of an Apollo spacecraft. Blockhouse personnel of the Kennedy Space Center's Government- industry launch team follows liftoff of uprated Saturn AS-20-3 on television monitors inside Complex 37 launch control center. Seated at a console and pointing (front center) i s Dr. Kurt H. Debus, Director of the Kennedy Space Center. Manning the peri scope directly behind Dr. Debus i s the Marshall Space Flight Center Director, Dr. Wernher von Braun. The launch control center i s located approximately 1,200 feet from the launch pad. Constructed of heavy reinforced concrete, the two story, dome shaped structure can withstand blast pressures of 2, 188 pounds per square inch. - - - �THE HUMAN ELEMENT �The John F. Kennedy Space Center i s many things. It i s the tremendous power of space vehicles carrying precious cargoes o f men and equipment; i t i s s c i e n t i f i c progress i n it i s material and hardwareaction; some minute and delicate, some huge and powerful-in various stages o f being born and growing up; i t i s a l l these and more. The John F. Kennedy Space Center i s also people. From N e w York City; Nashville, Tennessee; Dallas, Texas; San Jose, California-virtual ly from a l l over the United States-these people, representing a l l racial and ethnic backgrounds and professions and skills, have been molded into one o f the greatest teams ever assembled for a peacetime endeavor. More than 24,000 strong and representing the b e s t launch talent i n government and industry, t h i s team devotes i t s s k i l l s and talents to the United States' goal o f space preeminence. Additionally, thousands of Air Force Eastern T e s t Range personnel and A i r Force-associated con- ... tractor personnel are providing v i t a l range and mission support to NASA activities. Because the continuing progress of the space program i s dependent upon the total, coordinated efforts of many people, no task i s inconsequential, no job t r i v i a l and no individual unimportant. Each success hinges on the premise that the people involved w i l l do the best iob they know how to do a t a l l times. The entire space program i s varied and complex, as are the s k i l l s required to successfully accomplish the iob. Welders, radio technicians, doctors o f medicine, engineers, scientists, mechanics, tinsmiths, writers, photographers, truck drivers, policemena l l these and more are employed. T h i s i s but a fragment of the whole. As each day expands the scope and technology o f space activities, the need for people who can cope w i t h and contribute to the growth of the space program also expands. People are the most important asset o f the program. �PRIVATE INDUSTRY �BUDGET Research and Development of Ground-Support Equipment and Instrumentation Construction of Facil- $ 37,876,000 ities FACTS & FIGURES MANPOWER Federal Service Personnel Support Contractor Personnel Stage Contractor Personnel Corps of Engineers Personnel (C of E) Construction Workers NASA and NASA Related Manpower-July 1, 1967 $339,800,000 Administrative Operations Total Budget Estimate (Fiscal Year 1967) $ 93,620,000 $47 1,296,000 - GOVERNMENT INDUSTRY TEAM AT KENNEDY SPACE CENTER CONTRACTORS CONTRACTORS �8 PUBLIC BUS TOURS Daily bus tours of the Kennedy Space Center and Cape Kennedy are available to the public. Tours originate near the Center's Gate 3 , adjacent to U. S. Hwy. 1. The tour route includes the industrial and launch a r e a s of the Kennedy Space Center and Cape Kennedy Air Force Station, with s t o p s for photography and a v i s i t to the Vehicle Assembly Building. Nominal f e e s are charged for the tour. Tour information and reservations may be obtained by writing NASA Tours, P o s t Office Box 21222, Kennedy Space Center, Florida 32899. � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000061 Title A name given to the resource "America's Spaceport." Alternative Title An alternative name for the resource. The distinction between titles and alternative titles is application-specific. KSC-601 Description An account of the resource Guide to John F. Kennedy Space Center, including an introduction from Center director Kurt Debus. Creator An entity primarily responsible for making the resource John F. Kennedy Space Center United States. National Aeronautics and Space Administration Date A point or period of time associated with an event in the lifecycle of the resource 1967-09-01 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn Project (U.S.) John F. Kennedy Space Center Launch complexes (Astronautics) United States. National Aeronautics and Space Administration Astronautics--United States Outer space--Exploration Aeronautics--United States Type The nature or genre of the resource Pamphlets Text Source A related resource from which the described resource is derived Saturn V Collection Box 36, Folder 103 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000051_000074 https://digitalprojects.uah.edu/files/original/20/1144/spc_stnv_000060.pdf d62b3e42d82eaccd92efb30379a91002 PDF Text Text , - -> * I NATIONAL AERO;x.'AUTICS AND SPACE ADMINIS~RATIONI WO 9-41 5 5 VJAjl-I,:r'GTON, D.C. 20546 TELS' WO 3-6925 1 L3< J 1 - -. GSLil G , ' . Y- 7- f i F-u*-. *.-. 3 . r z (ACCESSION NL'hrtCR) . 3 1 1 > C f 4 9;ili L < ( N A S A C R OR TMX OR A D N U M U E R ) Address by James E. Webb, A d m i n i s t r a t o r N a t i o n a l Aeronautics and Space A d m i n i s t r a t i o n i I J I n v e n t o r s ' Congress and Space Symg?osiuin L i t t l e Rock, Arkansas October 30, 1964 I,, ' ,/ G e r i c a n Procrress and Goals i n Space \ I t i s h e a r t e n i n g t o p a r t i c i p a t e i n a meeting l i k e t h i s , one i n which i n v e n t o r s , i n d u s t r i a l r e p r e s e n t a t i v e s , and members of t h e S t a t e government cone t o g e t h e r t o exchange i d e a s . Such a c t i v i t i e s cannot f a i l t o spur expanding c r e a t i v e e f f o r t and more d i v e r s i f i e d i n d u s t r i a l p r o d u c t i o n i n t h i s s t a t e and r e g i o n . I a m e s p e c i a l l y p l e a s e d t o d i s c u s s t h e N a t i o n a l Space Program b e f o r e t h i s group t o n i g h t , A s p e r s o n s concerned w i t h i n v e n t i o n and development, you w i l l be e s p e c i a l l y I i n t e r e s t e d i n t h e space program, i t s s i g n i f i c a n c e t o t h e n a t i o n ' s p o s i t i o n of world l e a d e r s h i p , and i t s r e l a t i o n s h i p �to t h e growth of America i n a n age merked by e x p l o s i o n s of knowledge i n a wide v a r i e t y of s c i e n t i f i c and t e c h n i c a l f i e l d s . Much of t h e p r o g r e s s of t h e world h a s bccn based upon t h o s e c r e a t i o n s of hard work and i n s p i r a t i o n which w e c a l l inventions, times. T h i s i s no l e s s t r u e today than in e a r l i e r L e t m e i l l u s t r a t e by . k f e r e n c e t o t h e steam engine, a source of power on e a r t h , and t o t h e r o c k e t engine, t h e source o f power i n space, I t was James Watt who developed t h e f i r s t r e a l l y s u c c e s s f u l steam engine i n 1774, pursuing' a s a l o n e l y i n d i v i d u a l a c r e a t i v e idea. T h i s engine embodied t h e e s s e n t i a l f e a t u r e s of t h e modern steam engine. Watt's engine provided t h e power f o r t h e I n d u s t r i a l Revolution; it l e d t o r a i l r o a d s , t o steam-operated m i l l s and f a c t o r i e s , t o steaniboats and s h i p s f o r r i v e r and ocean commerce. The work o f D r . Robert H. Goddard w i t h p r i m i t i v e , liquid-powered r o c k e t s i n t h e 1 9 2 0 ' s and 1930's i n Massachusetts and New Mexico was i n t h e same p a t t e r n a s W a t t ' s work, His was no l e s s a n i n d i v i d u a l achievement, c a r r i e d o u t under d i s c o u r a g i n g circumstances. r o c k e t i n 1926 -- The f l i g h t of Goddard's f i r s t a t o t a l of 184 f e e t i n two and one h a l f seconds -- �-3- was one of t h e major e v e n t s l e a d i n g t o t h e f a n t a s t i c speed of about 25,000 m i l e s p e r hour f o r t o d a y ' s Venus and Mars probes t o d i s t a n c e s of m i l l i o n s of m i l e s i n t o deep space, and u l t i m a t e l y w i l l e n a b l e men t o e x p l o r e t h e moon and p l a n e t s . The power of c r e a t i v e i d e a s such a s D r . Goddard's and t h e a b i l i t i e s and w i l l i n g n e s s of men t o c a r r y them t o f r u i t i o n have been among t h e p r i n c i p a l a s s e t s of t h e United S t a t e s s i n c e i t s foundation. The r e v o l u t i o n a r y changes t h a t a r e t a k i n g p l a c e i n s c i e n t i f i c and t e c h n o l o g i c a l p e r s p e c t i v e s through t h e mastery of s p a c e open v a s t new realms f o r t h e c r e a t i v e a c t of i n v e n t i o n , and f o r t h e t r a n s l a t i o n of i n v e n t i o n t o p r a c t i c a l use. We must t a k e advantage of t h i s new s i t u a t i o n . As t h e N a t i o n a l Space Program moves i n t o i t s s e v e n t h y e a r , t h e United S t a t e s has reached t h e halfway p o i n t i n a broadb a s e d , a c c e l e r a t e d program f o r t h e p r e s e n t decade, a program t h a t w a s planned and h a s been c a r r i e d forward by t h r e e Adninistratiocs. L e t me b r i e f l y d i s c u s s w i t h you some of t h e major achievements and plans of t h i s program: o Manned s p a c e c r a f t f ~ cra r r y i n g crews i n n e a r - e a r t h o r b i t s of long d u r a t i o n , f o r i n v e s t i g a t i n g space outwsrd a q u a r t e r of a m i l l i o n m i l e s from t h e e a r t h , and f o r t a k i n g a s t r o n a u t s t o e x p l o r e t h e moon and t o r e t u r n them s a f e l y home. �-- ?dvanced, highly instrcmented, c n n ~ a n n e d s p z c e c r a f t ,,,,l..r.atically progranxned -- -,,,,h or remotely c o n t r o l l e d b y r a d i o from f o r m i s s i o n s m i l l i o n s of m i l e s deep i n space, i n c l u d i n g . ,-..,ftto examine t h e p l a n e t s e l e c t r o n i c a l l y , b y photography, *. ? ., t o transmit t h e information t o e a r t h s t a t i o n s . One .:;.:t 0 2 t h e s e extremely d i f f i c u l t f e a t s w i l l b e a t t e m p t e d nonth, d u r i n g a 30-day p e r i o d f o l l o w i n g Novefier 4. NASA launch two 570-pound Mariner s p a c e c r a f t t o f l y by t h e ? l a n e t Mars, j u s t a.s Nariner I1 f l e w b y Venus a b o u t two y e a r s a;o. Tne c h i e f d i f f e r e n c e , and it i s a b i g one, i s t h a t Venus x i s 3 6 m i l l i o n m i l e s d i s t a n t from e a r t h and Mars w i l l b e 1 5 0 r n i l l i ~ nmiles. about The Venus voyage took a l i t t l e over t h r e e months; t h e Mars f l i g h t w i l l r e q u i r e almost e i g h t and one-half Each of t h e s p a c e c r a f t apart -- w i l l -- which w i l l b e launched a few days c a r r y i n s t r u m e n t s f o r e i g h t s c i e n t i f i c experiments; s i x of t h e s e a r e designed t o measure r a d i a t i o n , magnetic f i e l d s , and 'micrometeorites i n i n t e r p l a n e t a r y space and near Mars. If a l l ' g o e s w e l l , a t e l e v i s i o n camera aboard each c r a f t w i l l t a k e up t o 22 s t i l l photographs of Mars, and a s p e c i a l d e v i c e t o determine t h e c h a r a c t e r i s t i c s of t h e &YIartianatmospheric p r e s s u r e '"ill be t u r n e d on. L ~ o r i e sa r e achieved, The t e l e v i s i o n p i c t u r e s , i f planned t r a j e c should be comparable i n d e t a i l w i t h photo- �graphs of t h e moon t a k e n by t h e b e s t e a r t h - b a s e d t e l e s c o p e s , These first p i c p e e r i n g m i s s i o n s c a n ~ o tprove or d . i s p r s v e t h e e x i s t e n c e of l i f e on K a r s , b u t t h e y can, i f s u c c e s s f u l , i n c r e a s e o u r knowledge of t h e p r o b a b i l i t i e s . We have had t~ /'success w i t h a s e r i e s of weather s a t k l l i t e s which have photographed from high above thousands of cloud p a t t e r n s , i n d i c a t i n g p r e v a i l i n g weather f r o n t movements. These s a t e l l i t e s i n c l u d e s o f a r e i g h t s f t h e T i r o s s e r i e s and one of t h e Nimbus series, I n a d d i t i o n t o cloud photos from t h e sunward s i d e of t h e e a r t h , some of t h e weather s a t e l l i t e s , n o t a b l y Nimbus, have employed i n f r a - r e d s e n s o r s t o map weather p a t t e r n s a t n i g h t . I n s t z l l e d on some of N A S A ' s e a r l i e s t s a t e l l i t e s were f o r e r u n n e r s of t h e i n s t r u m e n t s which have achieved such h i g h d e g r e e s a€ s u c c e s s f o r T i r o s and Nin-ibus, e We have r e f l e c t e d o f f t h e g i a n t , aluminized Echo b a l l o o n - s a t e l l i t e thousands of r a d i o , r a d i o - t e l e p h o n e , f a c s i m i l e , and o t h e r e l e c t r o n i c s i g n a l s -- photo- c l e a r messages between p o i n t s thousands of m i l e s a p a r t on t h e e a r t h ' s s u r f a c e , Echo i s a " p a s s i v e u s a t e l l i t e , a n o r b i t i n g " m i r r o r i n t h e sky" for electronic signals. e T e l s t a r , Relay, and Syncom a r e America's " a c t i v e n comunications s a t e l l i t e s . That i s , t h e y p i c k up from e a r t h s t a t i o n s s i g n a l s s f t h e r a d i o o r t e l e v i s i o n t y p e s , r e c o r d them �-6- ,,i 3 a g n e t i c t a p e s , t h e n r e t r a n s n i t t o distant p o i n t ? c n t h e q l c b e , l n Syncon we have t h e f i r s t s o - c a l l e d "stationary" s a t e l l i t e s which, s i n c e t h e y o r b i t a t 2 2 , 3 0 0 m i l e s above t h e e a r t h , hover aSove t h e same s p o t . s Our o r b i t i n g ~ b s e r v a t o r i e sof s e v e r a l t y p e s n o t o n l y study t h e e a r t h from above i t s atmosphere, a s we91 a s t h e sun and t h e s t a r s , b u t a l s o measure s o l a r and cosmic r a d i a t i o n and t h e f o r c e s of g r a v i t a t i o n and magnetism n e a r t h e e a r t h and t o v a s t d i s t a n c e s ~ u itn space, @ We a r e b u i l d i n g r e l i a b l e and v e r s a t i l e r o c k e t e n g i n e s t h a t w i l l develop tremendous t h r u s t s , r a n g i n g from 1.5 m i l l i o n pounds f o r S a t u r n I t o 7,5 m i l l i o n pounds f o r t h e S a t u r n V, These g i a n t pawer e n g i n e s w i l l b e c a p a b l e of c a r r y i n g o u t missions i n s p a c e r e q u i r e d by t h e n a t i o n a l i n t e r e s t s d u r i n g t h e p r e s e n t decade and perhaps f o r a longer p e r i o d . o The n l t i o n a l space program has e s t a b l i s h e d a world- wide t r a c k i n g and d a t a a c q u i s i t i o n network, 0 We have b u i l t and a r e b u i l d i n g o t h e r l a r g e ground f a c i l i t i e s f o r f a b r i c s t i n g , t e s t i n g , l a u n c h i n g , and c o n t r o l l i x g t h e new r o c k e t s and s p a c e c r a f t -- f a c i l i t i e s t h a t w i l l be b a s i c n a t i o n a l a s s e t s f o r many y e a r s t o come, a NASA r e s e a r c h and development c e n t e r s , s t a f f e d w i t h s k i l l e d �1 and experienced p e r s o n n e l , a r e s t u d y i n g what t h e United S t a t e s r e q u i r e s i n spzce and what i t can accon~?li.cii, A t t h e sarce time t h e s e p e r s o n n e l work with i n d u s t r y , where more t h a n 90 p e r c e n t of t h e NASA funds a r e s p e n t , i n t h e p r o d u c t i o n of t h e r o c k e t s , s p a c e c r a f t , and o t h e r equipment, o W e have augmented t h e n a t i o n ' s r e s e a r c h c a p a b i l i t i e s i n our u n i v e r s i t i e s by means of t r a i n i n g g r a n t s , f a c i l i t i e s g r a n t s , and r e s e a r c h g r a n t s and c o n t r a c t s . o The program h a s founded an i n d u s t r i a l b a s e t h a t c a n meet any n a t i o n a l needs i n space t h a t may develop, and many r e q u i r e m e n t s on earth. I t i s important t o n o t e t h a t NASA works v e r y c l o s e l y w i t h t h e A i r Force i n manned space f l i g h t , The Gemini two-man s p a c e c r a f t w i l l s e r v e t h e A i r Force a s a key element i n i t s ,Qnned O r b i t i n g L a b o r a t o r y prognam. The t o t a l NASA e f f o r t c o n t r i b u t e s technology, s c i e n t i f i c d e s c r i p t i o n of i t s s p a c e envirosment, and o p e r a t i o n a l e x p e r i e n c e t o a wide v a r i e t y of d e f e n s e projects. The Department of Defense, i n t u r n , s h a r e s a p p l i c a b l e knowledge from i t s m i l i t 3 r y p r o j e c t s with NASA, This exchange i s a n i n t e g r a l p a r t of t h e concept of a n a t i o n a l space progrm These a r e t h e n ? t i o n a l r e s o u r c e s a n d f a c i l i t i e s which t h e space program i s c r e a t i n g and p r ~ v i n go u t , They a r e of key importance t o the p r e c e n t s t r e n g t h and t o tka f u t u r e of t h e United S t a t e s , �The present r.39.e of EASA in aerona!-iticaland space research is a continuation and extension of that occupied. by its predecessor agency, the National Advisory Committee for ~eronautics, For more than 40 years, this civilian agency supgl.ied the basic scientific knowledge and technological development required to undergird our national requirements in aeronautics, both civil and military, and enabled the nation to assumeunquestiomlik supremacy in the air. Today, NASA is conducting research and development in support of every agency of the government which has, or may encounter, the need for operational activity in space. This includes the Weather Bureau in meteorological satellite operations, the Communications Satellite Corporation, and the Department of Defense. Ma:l's experience in space is limited, and all of the potential requiremezts and opportunities which it presents cannot yet be forsseen, But it is evident that they are there, And it is evident that not only we, bwt the Soviet Union and many other nations, also know they are there and intend to exploit them to enhance both their prestige and their power; Tha recent Soviet VosXh3d flight, during which three men �o r b i t e d t h e e a r t h i n a single s p a c e m f t , w a s a s i g n i f i c a n t space accomplishment, and a convincing demonstration t h a t t h e Russians i n t e n d t o p r e s s forward i n manned s p a c e f l i g h t a c t i v i t y . A t t h i s s t a g e i n t h e space e f f o r t , t h e S o v i e t Union c o n t i n u e s t o e n j o y t h e advantage i n o p e r a t i o n a l r o c k e t power t h a t i t h a s h e l d s i n c e t h e o u t s e t of t h e Space Age. c a t c h i n g up. But we a r e The 1 . 5 m i l l i o n pound t h r u s t S a t u r n I launch v e h i c l e , a l r e a d y s u c c e s s f u l l y f l i g h t t e s t e d on seven o c c a s i o n s , c a p a b l e of p l a c i n g 38,700 pounds i n e a r t h o r b i t . The S a t u r n V, now under development, w i l l g e n e r a t e 7.5 m i l l i o n . . pounds of t h r u s t and p l a c e 240,000 pounds i n t o e a r t h o r b i t , and it w i l l a l s o launch our e x p l o r e r s t o t h e moon. Let me add a arm-d about t h e Apollo program, which h a s l u n a r e x p l o r a t i o n a s one of i t s g o a l s . I t i s imoortant t h a t e v e r y ~ m e r i c a nr e c o q n i z e t h a t t h e fundamental o b j e c t i v e of t h e Apollo program, and of t h e e n t i r e n a t i o n a l s p a c e e f f o r t , pre-eminence i n s p a c e , and n o t t h e achievement of any s i n g l e s p e c i f i c goal. To a c h i e v e space l e a d e r s h i p , t h e n a t i o n must d e v e l o p t h e f a c i l i t i e s , t h e technology, t h e s c i e n t i f i c knowledge and t h e a b i l i t y t o o p e r a t e i n s p a c e a s we have �l e a r n e d t o o p e r a t e on t h e l a n d , s e a , and i n t h e a i r . I t i s e s t i m a t e d t h a t 90 p e r c e n t of t h e e x p e n d i t u r e s b e i n g made i n t h e Apollo program would be r e q u i r e d t o a c h i e v e pre-eminence i n s p a c e , even i f we had no i n t e n t i o n of going t o t h e moon. Moreover, y e a r s of o r d e r l y e x p e r i m e n t a l f l i g h t w i l l be conducted i n o r b i t near t h e e a r t h , b e f o r e t h e f i r s t a s t r o n a u t s set o f f f o r t h e moon. We w i l l l e a r n t o maneuver i n s p a c e , t o j o i n s p a c e c r a f t i n o r b i t , t o f l y o u t a t w i l l and return a t w i l l . Although one o b j e c t i v e i s t h e moon, t h e n a t i o n w i l l accumulate some 5,000 man h o u r s of f l i g h t i n n e a r - e a r t h o r b i t b e f o r e t h e f i r s t a t t e m p t i s made t o launch Apollo t o t h e moon. That i s almost 100 t i m e s t h e e x p e r i e n c e i n e a r t h o r b i t which was accumulated by a l l of our a s t r o n a u t s d u r i n g a l l o f the f l i g h t s i n t h e Mercury program. The i m p l i c a t i o n s of t h i s e x p e r i e n c e , and t h e a c q u i s i t i ~ n of t h i s o p e r a k i o n a l s k i l l f o r b o t h c i v i l i a n s p a c e programs and t h o s e o f t h e Department of Defense, a r e a p p a r e n t , The United S t a t e s space program h a s y i e l d e d f o r t h i s n a t i o n one s i g n i f i c a n t b e n e f i t which t h e Russians have n o t been a b l e t o g a i n from t h e i r s e c r e t space a c t i v i t y . It h a s �becorns a s i g n i f i c a n t force E c r i n t e r n a t ions: 2 0 - o ~ ~t ri oa n between t h e U n i t e d S t a t e s and o t h e r n a t i o n s of t h e w o r l d , and s t r e n g t h e n e d o u r t i e s n o t o n l y w i t h o u r F r e e \j?orld a l l i e s , b u t w i t h many o f t h e ercerging n a t i o n s . NASA c u r r e n t l y h a s 2 2 o p e r a t i o n a l t r a c k i n g and d a t a a c q u i s i t i o n s t a t i o n s l o c a t e d i n 1 8 d i f f e r e n t counizries, with t h r e e additional locations a g r e e d u p n b u t not y e t operational. Such s t a t i o n s r e 2 r e s e n t c o m o n e f f o r t s and c e n t e r s f o r c o n t i n u e d growth of u n d e r s t a n d i n g and c o - o p e r a t i o n . Three i n t e r n a t i o n a l s a t e l l i t e s which w e r e c o n c e i v e d , d e s i g n e d , f i n a n c e d and e n g i n e e r e d abroad -- A r i e l I and I1 f o r t h e B r i t i s h and A l o u e t t e I f o r t h e Canadians been l a u n c h e d by NASA. -- have Additional s a t e l l i t e launchings a r e s c h e d u l e d f o r b o t h of these c o u n t r i e s a s w e l l a s f o r t h e F r e n c h , I t a l i a n s and t h a European S2ace R e s e a r c h O r g a n i z a t i o n . N i n e French and B r i t i s h e x p e r i m e n t s a r e scheduleii f o r i n - c l u s i o n on NASA s a t e l l i t e s which w i l l be l a u n c h e d over t h e n e x t few y e a r s . NASA h a s c a r r i e d o u t 65 c o - o p e r a t i v e l a u n c h i n g s of sounding r o c k e t s w i t h 11 c o u n t r i e s , and c u r r e n t l y has �,greements w l t h t h r e e a d d i t i o n a l c o u n t r i e s f o r such p r o j e c t s . I n a d d i t i o n , 41 c o u n t r i e s a r c now p a r t i c i p a t i n g i n N A S F ' S m e t e o r o l o g i c a l s a t e l l i t e p r o j e c t s , c o n d u c t i n g s p e c i a l sbs e r v a t i o n s of l o c a l w e a t h e r c o n d i t i o n s a t t h e i r own e x p e n s e which a r e s y n c h r o n i z e d w i t h the p a s s e s o f U . S. w e a t h e r satellites. Seven c o u n t r i e s have a l r e a d y b u i l t e x p e n s i v e ground t e r m i n a l s and conductzd t e s t t r a n s m i s s i o n s i n connect i o n w i t h o u r communications s a t e l l i t e program, and a g r e e ments have been r e a c h e d w i t h f o u r o t h e r c o u n t r i e s . You a r e a l l f a m i l i a r , I am s u r e , w i t h t h e c o - o p e r a t i v e a r r a n g e m e n t s rsached w i t h Japan providing f o r d i r e c t t e l e v i s i o n coverage of t h e Olympic Games v i a t h e Syncom s a t e l l i t e . I n t e r n a t i o n a l p e r s o n n e l exchanges, which p r o v i d e f o r d i r e c t c o n t a c t s between s c i e n t i f i c and t e c h n i c a l p e r s o n n e l , c o n t r i b u t e i m p o r t a n t l y t o a l l o f t h e above c o - o p e r a t i v e efforts. Under t h e XASA f e l l o w s h i p program, t h e s p o n s o r i n g c o u n t r y pays for t h e t r a v e l and s u b s i s t e n c e o f i t s t r a i n e e s . T h i s r e q u i r e r e n t f o r investment on t h e p a r t of t h e p a r t i c i pating country assures careful consideration of t h e personnel s e l e c t e d and t h e i r f u t u r e u t i l i z a t i o n when t h e y r e t u r n . C o s t s o f i n s t r u c t i o n a r d borne by XASA. �A t the present time, t h e r e a r e 9 2 I n t e r n a t i o n a l Research E z s s o c i a t e s i n NASA c e n t e r s , 44 I n t e r n a t i o n a l Graduate ?ello-v?s i n U. S. U n i v e r s i t i e s , and 176 f o r e i g n t e c h n i c a l t r a i n e e s a t NASA c e n t e r s i n s u p p o r t of c o - o p e r a t i v e p r o j e c t s and ground f a c i l i t y o p e r a t i o n s , I n addition t o the formal exchanges, EASA and i t s c e n t e r s are h o s t s t o numerous foreign v i s i t o r s , U p t o J u l y 1 of t h i s y e a r , t h e r e had been 8 , 4 0 0 such v i s i t o r s from 95 c o u n t r i e s ; 1,900 d u r i n g t h e l a s t s i x months. T h e s p a c e program i s producing new s c i e n t i f i c knowledge w i t h wide i m p l i c a t i o n s f o r p r a c t i c a l use. A n o f f i c i a l of t h e Westinghouse A i r Brake Company was quoted t h i s week t h a t "Space r e s e a r c h i s c r e a t i n g a ' t e r r i f i c f a l l o u t ' of b a s i c knowledge which o l d e r i n d u s t r i e s a r e t r y ing t o u t i l i z e , " I n a d d i t i o n , t h e ailvances i n technology r e q u i r e d t o b u i l d , launch and o s e r a t e t h e b o o s t e r s and s p a c e c r a f t are p r o v i d i n g t h e base f o r much of t h e technology of t h e f u t u r e : i n materials, i n e l e c t r o n i c s , i n processing, i n r e l i a b i l i t y , and i n v i r t u a l l y e-7ery f i e l d of technology, �AS of S e p t e n b e r 1, 1 9 6 4 , EASA had r e c e i v e d from a l l s o u r c e s 3 , 5 1 9 d i s c l o s u r e s of i n v e n t i o n s b e l i e v e d t o p o s s e s s patentable novelty. TWOthousand two hundred and f o r t y of t h e s e were r e c e i v e d from c o n t r a c t o r s and 1 , 2 7 9 from N A S A ' s own employees. Of t h i s t o t a l , 2 , 1 1 1 d i s c l o s u r e s have been placed i n the inactive f i l e s , One thousand f o u r hundred and e i g h t d i s c l o s u r e s were a c t i v e a s o f September 1. Of t h e s e , 508 a r e t h e s u b j e c t s of p a t e n t a p p l i c a t i o n s . One of NASA's own i n v e n t o r s i s Mrs. B a r b a r a Lunde. T h i s a t t r a c t i v e 26-year-old aerospace engineer-housewife works a t o u r Goddard Space F l i g h t C e n t e r , i n Maryland, just o u t s i d e Washington, Mrs. Lunde h a s two p a t e n t a p p l i c a - t i o n s b e i n g c o n s i d e r e d b y t h e P a t e n t O f f i c e and h a s d i s c l o s e d f o u r more f o r c o n s i d e r a t i o n . Her i n v e n t i o n s i n c l u d e two v a l v e s , f o r s p a c e c r a f t , :.~hich have no moving p a r t s , Tomorrow, M r . Breene Kerr w i l l t e l l you i n d e t a i l of t h e NASA Technology U t i l i z a t i o n grogram d e s i g n e d t o make a l l o f t h e s e advances q u i c k l y a v a i l a b l e t h r o u g h o u t t h e K a t i o n , I u r g e you t o t a k e f u l l advantage of t h i s program i n A r k a n s a s . I t i s o f major i m ~ o r t a n c et o your economic f u t u r e . Bear i n �,ind t h a t it t o o k 112 years t o d e v e l o p photography t o a n d e g r e e , 56 y e a r s t o d e v e l o p t h e t e l e p h o n e , 35 y e a r s t o p e r f e c t t h e r a d i o , 15 years t o develop r a d a r . Television took 12 y e a r s , t h e a t o m i c bomb s i x and t h e t r a n s i s t o r f i v e . I n t h i s c o n n e c t i o n , it i s of s i g n i f i c a n c e t o t h e S t a t e of Arkansas t h a t a major p a r t of t h e n a t i o n ' s s p a c e i n s t a l l a - t i o n s a r e a l r e a d y f u n c t i o n i n g t o t h e s o u t h and e a s t of your State. I r e f e r t o what h a s been c a l l e d t h e S o u t h e r n C r e s c e n t of t h e s p a c e program. The f i r s t o f t h e s e i s t h e Cape Kennedy complex, t h e major s i t e f o r t h e l a u n c h i n g of o u r l a r g e r o c k e t s . This i s a permanent i n s t a l l a t i o n , a major e l e m e n t i n t h e n a t i o n ' s c a p a c i t y t o go i n t o s p a c e . It is already a large f a c i l i t y and i s b e i n g expanded g r e a t l y t o accommodate t h e l a r g e S a t u r n r o c k e t s which w i l l c a r r y o u r a s t r o n a u t s t o t h e moon. To g i v e you some i d e a o f t h e s c o p e o f t h i s u n d e r t a k i n g : d u r i n g t h e p a s t t h r e e F i s c a l Years some 700 m i l l i o n d o l l a r s was a p p r o p r i a t e d f o r c o n s t r u c t i o n of NASA f a c i l i t i e s a t Cape Kennedy. �The second p a r t of t h i s development i s t h e M a r s h a l l Space F l i g h t C e n t e r a t H u n t s v i l l e , Alabama. There some 6 , 5 0 0 p e o p l e a r e a t work, p r i m a r i l y engaged i n b u i l d i n g t h e f i r s t of t h e g r e a t S a t u r n r o c k e t s , w i t h t o t a l o p e r a t i n g c o s t s f o r t h e c u r r e n t F i s c a l Year o f over 100 m i l l i o n d o l l a r s , and w i t h a c o n s t r u c t i o n program a b o u t a t h i r d a s l a r g e . The t h i r d p a r t i s found i n a complex a t Michoud, L o u i s i a n a , and i n n e a r b y s o u t h e r n M i s s i s s i p p i . A t Michoud, a World War I1 a i r c r a f t p l a n t , a l r e a d y owned by t h e Government, i s b e i n g used t o b u i l d t h e f i r s t s t a g e s of t h e S a t u r n I-B and S a t u r n V r o c k e t s , persons. I t employs o v e r 1 1 , 0 0 0 Not f a r from Michoud i s b e i n g c o n s t r u c t e d t h e M i s s i s s i p p i T e s t F a c i l i t y , where t h e S a t u r n r o c k e t s w i l l b e checked o u t and t e s t e d t h o r o u g h l y . I n t i m e , some 3 , 3 0 0 s c i e n t i s t s , e n g i n e e r s , and t e c h n i c i a n s and s u p p o r t w o r k e r s w i l l b e a t work a t t h i s massive f a c i l i t y . The l a s t p a r t i s a t Houston, where t h e Manned S p a c e c r a f t Center i s being constructed. This, l i k e t h e o t h e r s t h a t I have c i t e d , i s a permanent i n s t a l l a t i o n d e s i g n e d t o be t h e c e n t e r f o r a l l o f o u r e f f o r t s t o s e n d man i n t o s p a c e . �c u r r e n t l y , t h ~ r ea r e mar@ "Lha.11 4,000 p n o p l ~eit .sror!r a t the Houston C e n t e r , and q u i t e l i k e l y t h i s number will i n c r e a s e in t h e f u t u r e . One o f t h e c e n t r a l f a c t s about t h i s g r e a t complex of space a c t i v i t i e s t h a t I have d e s c r i b e d i s t h e p o s s i b i l i t y t h a t many v a r i e d research, developmant and p r o d u c t i o n activities w i l l gravitate in t h i s direction. T h i s i s made l i k e l y by r e a s o n s of economics and of convenience. By and l a r g e , t h e s e w i l l be a c t i v i t i e s t h a t r e q u i r e heavy c o n t r i b u t i o n s from s c i e n c e and technology, and Arkansas and t h e o t h e r s t a t e s of t h e South a r e now i n a p o s i t i o n t o g e t r e a d y t o t a k e f u l l advantage of the p r o s p e c t . Arkansas must b e a b l e t o advance i n such a r e a s a s e l e c t r o n i c s , i n t h e development and use of new m a t e r i a l s , i n medical r e s e a r c h r e l a t e d t o t h e s e v e r e r e q u i r e m e n t s of s p a c e , and the like. I t must n o t only make p r o v i s i o n s f o r s u i t a b l e working art! l i v i n g c o n d i t i o n s f o r s c i e n t i s t s and e n g i n e e r s , it must a l s o be f a r - s i g h t e d i n t r a i n i n g i t s people a s t e c h n i c i a n s and s k i l l e d workmen, f o r t h e s e are a s e s s e n t i a l i n t h i s k i n d of a c t i v i t y a s t h e s c i e n t i s t s and e n g i n e e r s . �I n conclcsion, I w o u l d l i k ? t o emphasize that -just as t h s devslopment of t h e autornobil*: and the a i r c r a f t i n d u s t r i z s r e s u l t e d i n a g r e a t e r and s t r o n ~ e rn a t i o n a l economy acd provi3ed nevv j o b s f o r m i l l i o r . ~ , o u r v e n t u r e i n t o s p a c e i s s t i m u l a t i n g t e c h n o l o g y and s p u r r i n g o u r economy toward new and g r e a t e r h e i g h t s . Furthe?more, o u r s p a c e prograni i s enhancing t h e n a t i o n ' s c d u c s ? i o n a l s t a n d a r d s a t a t i m e when the ray.id advance of t e c h r . c _ i s g i c a l achievement makes even g r e a t e r demands upon e d u c a t i n n . Faen w e add the w i l l and t h e d e t e r m i n a t i o n o f Americans, a s i n d i v i d u a l s and a s a p e o > l e , and t h e i n g e n u i t y of o u r government-industry-v1niver5ity complex, w e have a program f o r t h e s u c c e s s f ~ le x p l o r a t i o n of s p a c e f o r t h e b e t t e r m e n t of a l l mankind. � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000060 Title A name given to the resource "American Progress and Goals in Space," address by James E. Webb. Description An account of the resource This address was given by James E. Webb, Administrator, National Aeronautics and Space Administration, at the Inventors' Congress and Space Symposium, Little Rock, Arkansas. Creator An entity primarily responsible for making the resource Webb, James E. (James Edwin), 1906-1992 United States. National Aeronautics and Space Administration Date A point or period of time associated with an event in the lifecycle of the resource 1964-10-30 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn Project (U.S.) Astronautics and state--United States Space race United States. National Aeronautics and Space Administration Type The nature or genre of the resource Speeches Text Source A related resource from which the described resource is derived Saturn V Collection Box 12, Folder 32 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Is Part Of A related resource in which the described resource is physically or logically included. NASA News Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000051_000074 https://digitalprojects.uah.edu/files/original/193/13794/Defense_Billboard_124_001.pdf 84605ef7fc39c9448964800815d77560 PDF Text Text American Forces Information Service • Department of Defense 601 N.Fairfax Street Suite 312.• Alexandria. VA 223H-2007 •(7031428-0283, DSN 328-0283 � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Defense Billboard Posters Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context Defense_Billboard_124 Title A name given to the resource "Amphetimines; Get nowhere fast" Alternative Title An alternative name for the resource. The distinction between titles and alternative titles is application-specific. D2.9:D36/2/No.124 Description An account of the resource Man going crazy taking a pill Creator An entity primarily responsible for making the resource Department of Defense Date A point or period of time associated with an event in the lifecycle of the resource 1998-04-29 Temporal Coverage Temporal characteristics of the resource. 1990-1999 Subject The topic of the resource Department of Defense poster United States--Department of Defense Amphetamine abuse Drug addiction Dogs Type The nature or genre of the resource Posters Still Image Source A related resource from which the described resource is derived The University of Alabama in Huntsville M. Louis Salmon Library Defense Billboards Posters Case 1, Drawer 1 Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource Defense Billboards https://digitalprojects.uah.edu/files/original/9/1215/spc_dann_000211.mp4 f1b1f5917bf9dd586637639766bdacb8 Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Konrad Dannenberg Collection Identifier An unambiguous reference to the resource within a given context Konrad Dannenberg Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/99">View the Konrad Dannenberg Collection finding aid on ArchivesSpace</a> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_dann_000211 MC_43_095 Title A name given to the resource "An afternoon walk thru the farm." Description An account of the resource Konrad and Ingeborg Dannenberg visit Alma's farmhouse. Shown are clips of George playing in the grass and others walking around the farm. Fall 1967. Creator An entity primarily responsible for making the resource Dannenberg, Konrad Date A point or period of time associated with an event in the lifecycle of the resource 1967-09-10 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Dannenberg, Konrad Family vacations German Americans Format The file format, physical medium, or dimensions of the resource 8 mm (photographic film size) Type The nature or genre of the resource Home movies Moving Image Source A related resource from which the described resource is derived Konrad Dannenberg Collection University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Provenance A statement of any changes in ownership and custody of the resource since its creation that are significant for its authenticity, integrity, and interpretation. The statement may include a description of any changes successive custodians made to the resource. Donated by Klaus Dannenberg. Digitized for the 2019-2020 CLIR Recordings at Risk grant. Language A language of the resource de en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource clir_grant_film_metadata_01 https://digitalprojects.uah.edu/files/original/20/10969/Iterguidscheitsappllunaland_081407120855.pdf aec119c87f8e9f99cfeb0abe4e897df7 Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context Iterguidscheitsappllunaland.pdf spc_stnv_000348 Title A name given to the resource "An Iterative Guidance Scheme and Its Application to Lunar Landing." Alternative Title An alternative name for the resource. The distinction between titles and alternative titles is application-specific. TN D-2869 Description An account of the resource A guidance scheme for vehicle flight from lunar orbit to a prescribed point on a spherical, non-rotating moon is presented. The equations of motion have been simplified only to perm it a closed solution for the thrust magnitude and thrust direction. The trajectory computations them selves are made under more realistic and accurate assumptions and are not included. Creator An entity primarily responsible for making the resource Horn, Helmut J. Date A point or period of time associated with an event in the lifecycle of the resource 1965-07-01 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn project Lunar landing Spacecraft guidance Space vehicles--Guidance systems Type The nature or genre of the resource Text Guidence Schemes Source A related resource from which the described resource is derived Saturn V Collection Box 14, Folder 22 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000325_000349 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. <a href="http://libarchstor.uah.edu:8081/repositories/2/archival_objects/17169"> View this item in ArchivesSpace. </a> https://digitalprojects.uah.edu/files/original/20/1146/spc_stnv_000062.pdf 8efd923cf171c8ba40ec870024c5ba75 PDF Text Text ANALOG SIMULATION 0 STAGE PROPULSION SYSTEM DYNAMIC CHARACTERISTICS J. W. L e h n e r Senior E n g i n e e r C h r y s l e r C o r p o r a t i o n Huntsville Ope r a t i o n s �Analog Simulation of Saturn S-IB Stage Propulsion System Dynamic Characteristics ABSTRACT The purpose of this paper is to present the the development of an analog computer model to sion system dynamic characteristics. tions a r e included. employed in stage propulassump- INTRODUCTION The propulsion model was developed to investigate the possibility of sustained ongitudinal oscillations occurring a t any time during f i r s t stage powered . It was designed to be used in conjunction with a dynamic struce propulsion system feed back (closed-loop) behavior. This phenomenon occurs when propellant tank fluid pressure perturbations (transmitted through the propulsion system) a r e sufficient to be amplified by propulsion system/structure interaction. The propulsion system to be described is defined as the fluid-mechanical components from the propellant tank bottoms through the H-1 engines. This system is composed of eight engines (four non-gimbaled inboard engines and four gimbaled outboard engines) and sixteen feed lines (two per engine). However, only one feed lineengine system is simulated and used a s representative. It is presented in two parts, feed lines and engine, to best project the methods and logic involved. Schematics a r e presented which illustrate the physical characteristics of each system. Numerical designations a r e assigned to each liquid-mechanical line segment interface and power generating subsystem location. The resulting system subdivisions a r e modeled individually using their respective numerical designations as the subs criptive nomenclature for model formulation. Analytical and empirical methods a r e used to describe each subsystem. The lumped parameter technique is used to define fluid dynamic and turbine-turbopump dynamic characteristics. Characteristic equations simulate pump, turbine and combustion chamber steady state performance. Other specially derived techniques (not developed in this paper) a r e used to describe line elasticity and combustion chamber pressure time delays. These equations a r e then combined, in the manner illustrated in logic diagrams, to form dynamic math models of the feed lines (LOX and fuel) and engine . System peculiarities such a s pump inlet cavitation compliance, pump dynamic gain, feed line fluid-structure interconnect and combustion chamber pressure delay were investigated in separate special studies to determine their influence on system �response. These studies were performed using test methods in conjunction with computer model studies. The results were inconclusive; however, assumptions were made that reduced the effect of the resulting model deficiencies. These assumptions a r e delineated in the following system descriptions. Method of Fluid-Mechanic System Analysis The fluid-mechanical systems to be described a r e subdivided into individual line segments of a size less than a 30 cps one-quarter wave length to allow for an acceptable frequency response range of 0-30 cps . The location of each segment was dictated by simulation requirements . Their dynamic properties, inertance (I), capacitance (C) and resistance (R), were individually lumped a s illustrated in Figure 1 to permit the following treatment. Fluid inertance, that property of fluids which resists acceleration, appears in the general flow equation which expresses fluid flowrate ( W - lb/sec) a s a function of inertance ( I - sec2/in2) and the pressure differential [ (pi-p0-&) - lb/in2 1 available for fluid acceleration: Inertance is calculated using line (segment) length (L - inches), line cross-sectional a r e a (A - in2) and the gravity constant ( g = 386.4 in/sec2) a s follows: A fluid flowing through a container will experience a pressure drop due to resistance resulting from fluid viscosity and/or momentum losses. The effect of this resistance (R - sec/in2) is reflected in the following equation: where the resistance is calculated from known flow conditions by: Capacitance is that property of a fluid-mechanical system which accounts for system elasticity. This t e r m is a function of both fluid and container (line) elasticity. However, in most cases for this model, line influence is insignificant. The effect on system behavior is characterized by the following ecpation: �where the capacitance (C - in2) is calculated using container volume (V - in3), fluid specific weight (Q - 1b/in3) and fluid-mechanical system effective bulk modulus ( - lb/in2) a s follows : teff The term geff includes the effect of line elasticity and is determined as a function of fluid bulk modulus ( p ) , line diameter (D = inches), line thickness ( t - inches) and line modulus of elasticity (E - lb/in2) by: It was necessary in some cases to use effective values of inertance and capacitance due to varying segment (line) geometry. These values were calculated by dividing the segment into smaller parts , calculating the values of the respective parameters, and then combining these by the following equations to arrive at an effective magnitude: Equations 1-3 were combined for computer programming in the manner illus trated in Figure 2, to form a single segment model. System Description 1) Feed Line Simulation The feed lines, illustrated in Figure 3 as typical, a r e subject to a wide range of dynamic disturbances. All significant disturbances a r e expected to originate as pressure perturbations at the tank bottom. However, the complex construction (gimbal joints, expansion joint and bends) of the line exposes the fluids to various other dis turbances initiated by line motion. A four segment model, illustrated in Figure 4 , was developed to investigate the effects of these nebulous disturbances. Propellant cavitation exists for some distance upstream of the pump. The degree of cavitation is dependent on pump and propellant operating conditions and is influenced by line geometry. Its effect on fluid dynamic behavior is that of a soft complex non-linear spring. This effect is simplified for simulation by assuming the cavitation bubbles to be localized at the pump inlet as a single bubble with constant linear spring characteristics. This is accomplished with capacitance C4-5 shown in Figure 4. �Line Segment 7 Capacitance \-- Resistance Following Segment Line Segment Analogy Figure 1 ! i Typical Line Segment Figure 2 Single Element Simulation Tank Sump YimbdJoint FmiZir:-i -Prevalve I I ----------L Expansion Joint I L Figure 3 Typical Propellant Feed Line Simulation I - - Pump - - - - - - - - -J Figure 4 Typical Feed Line Simulation �The values used for C4-5 establish feed line resonances and correspondingly equal propulsion system resonances. This condition is illustrated in Figure 11 for a feed line resonant frequency of 15 cps. 2) Engine Simulation The H-1 rocket engine system schematic, Figure 5, illustrates the numerical designation assigned to each liquid-mechanical segment interface and power generating subsystem (thrust chamber, etc.) location, as well as other essential engine characteristics. The system subdivisions were modeled individually using their respective numerical designation a s the subscriptive nomenclature for model formulation. As illustrated, the engine propellant flow subsystem is subdivided into LOX segments L5-6, L6-7, L8-9 and L7-10 and fuel segments F5-6, F6-7, F7-8, F8-8', F8 ' -9 and F7 -10. These segments, with the exception of L5-6 and 5'5-6 (the LOX and fuel turbopumps), a r e modeled using the lumped parameter technique described previously. The models a r e then combined in the manner illustrated in Figure 7 where the inertance characteristic is represented by: and the capacitance by: to provide the necessary flow and pressure conditions for the combustion chambers (thrust and gas generator) and pump descriptions. The LOX and fuel turbopumps a r e simulated using equations derived from H-1 engine nominal steady state performance characteristic curves typically illustrated in Figure 8 . These equations do not account for pump performance variation due to perturbations in inlet conditions, but a r e sufficient since such variations a r e considered small as compared to the normal operating level. The equations a r e of polynominal second order form and satisfactorily approximate the performance characteristics where pump pressure head (AP)is a function of pump flowrate @ - lb/sec) and pump speed (& - rpm) a s follows : The shaft torque required to maintain the flow conditions of equation 8 is: �where pump efficiencies (LOX and fuel) (Eff) vary only a small amount and are usually assumed constant. Q is an empirical constant used to adjust the equation to any necessary condition. Equation 8 is used to derive A P L ~ and - ~ APF5+ and equation 9 defines T L and ~ T L .~ Combustion chamber characteristics a r e derived from chamber geometry and combustion products in the form of characteristic exhaust gas velocity (C*) . This term (C*) defines a relationship between pressure, flowrate and mixture ratio a s illustrated by Figure 9 and the general rocket engine relationship in which injector end combustion pressure (PI - psi) is a function of C*, total flowrate - lb/sec), chamber throat area (4- in2) and the gravitational constant (g - in/sec2). Steps were taken to reduce the algebraic content of the defining relationships to a minimum for analog application. In the case of the thrust chamber at a nominal mixture ratio of 2.33 pressure is predominantly a function of total propellant flowrate, and has only a minute response to expected mixture ratio changes about the nominal. For these reasons, thrust chamber steady state pressure is adequately defined by the following linear relationship: NT P'g = f@g) = K67g (11) where K is an empirical constant and may be determined simply by Gas generator combustion performance is a strong function of both mixture ratio and total flowrate. The gas generator operates fuel rich in a region (MR, = .342) well below the stoichiometric mixture ratio. As is apparent from a study of the C* curve trend, this operating condition causes the gas generator (GG) to be exceptionally sensitive to ratio changes. Consequently, a performance perturbation (about a nominal) model of the GG was developed to enhance analog computer accuracy. The resulting equations are: 6). The subscript N designates nominal values of mixture ratio (MR) and flowrate Subscripts L and F represent LOX and fuel, respectively, and their omission represents a combined o r total value. Combustion delay time and chamber pressure lag time a r e simply represented �by a pure time delay: and a first order lag: and a r e incorporated into equations 11 and 12 to simulate essential combustion dynamic behavior as follows : Values of T l and 7 a r e determined from propellant, chamber and operating characteristics. A constant value of '7 l is used and is calculated at nominal operating conditions a s : where Vol is chamber volume (in3), At is the chamber exit throat area (in3) and vn is the nominal gas exit velocity. A special study was performed to determine the value of -y . Turbine operating performance is a function of inlet and outlet gas characteristics and of turbopump speed. Exit gas behavior is assumed constant for dynamic turbine operation. Turbine inlet gas characteristics, pressure, temperature, weight flowrate and inlet gas velocity a r e defined as functions of chamber flowrate and mixture ratio to simplify the expression for turbine torque perturbation (nTlO). These characteristics a r e combined with turbine hardware characteristics and turbopump speed perturbations (&N6) to give : Included in the above equation is power lost due to gearbox resistance. Turbine torque is used along with total turbopump required torque p6)to define turbopump speed perturbations a s : �where 110, 6 is the combined inertance property of the turbopump, gearbox and turbine, and T6 is determined from: Total turbopump speed is defined as: Engine thrust is determined from the general rocket engine relationship: Chamber throat area (Ag - in2) and thrust coefficient (CFg) a r e assumed constant. The individual engine equations were integrated in the manner illustrated in Figure 7, to establish the engine dynamic model. 3 Propulsion System Simulation The three models were then combined a s shown in Figure 6 and programmed on an analog computer to produce single engine results which a r e graphically illustrated in Figures 10 and 11, as gain (dbs) versus frequency. These results were obtained to establish the individual effects of the LOX and fuel feed lines resonant conditions on propulsion response. This was accomplished by sinusoidally perturbing, separately, the LOX and fuel feed line inlets while systematically varying their respective resonant frequencies. Propulsion system total thrust (FT) is determined by the relationship which describes inphase engine operation, a desired worse case condition. A more detailed description of the individual equations, along with special derivations of combustion pressure delay (T,7')and effective fluid bulk modulus (peff) a r e presented in Chrysler Technical Report No. HSM-R181. �Fuel (RP-1) LOX Figure 5. 200K H-1 Engine Schematic , A P ~ l LOX Feed Line {-r PL5 WLS APF~/ , > H-1 Engine Model ---- 1 ::ast IB ' ___+ Typical System Engine -- Figure 6 . Propulsion System Simulation ��Volumetric Flow Rate (GPM) I 2400 . 3000 L 4000 Figure 8 . LOX Pump Developed Head Versus Volumetric Flow Rate and Speed *Extracted from Rocketdyne Technical Manual No. R-1352P-3 0 r Q) G ic^ 2. h .r( c1 8 $ 4 0 3 m .r( k a, +-, 0 ; & U Mixture Ratio (MR) 1 2.0 # 2.2 I 2.4 Figure 9. Characteristic Velocity Versus Injector End Chamber Pressure and Mixture Ratio 1 2.6 �� Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000062 Title A name given to the resource "Analog Simulation of Saturn S-IB Stage Propulsion System Dynamic Characteristics." Description An account of the resource This copy has handwritten notes that change the title to read, "Analog Simulation of Uprated Saturn I Stage Propulsion System Dynamic Characteristics." The abstract notes, "The purpose of this paper is to present the techniques and logic employed in the development of an analog computer model to simulate Saturn IV first stage propulsion system dynamic characteristics. Restraints, problem areas, and major assumptions are included." Creator An entity primarily responsible for making the resource Lehner, J. W. Chrysler Corporation Date A point or period of time associated with an event in the lifecycle of the resource 1966-11-01 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn Project (U.S.) Saturn launch vehicles Electric analog computers Analog computer simulation Analog computers Spacecraft propulsion Type The nature or genre of the resource Reports Text Source A related resource from which the described resource is derived Saturn V Collection Box 19, Folder 29 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000051_000074 https://digitalprojects.uah.edu/files/original/20/1147/spc_stnv_000063.pdf 4f6b05a7994bd629cc076c96c8443e3d PDF Text Text SATURY UlSTORY DOCUMENT University of Alabama Research Institute Histofy OF Science & Techrloloyy Group -- Date - - - - - . - - - - DOC NO. - - -"ANALYSIS AND PROJECTIONS O F S P A C E VEHICLE AUTOMATIC CHECKOUT ANC L 4UNCH" by C. R. Vedane T e c h n i c a l S y s t e m s Office G e o r g e C. M a r s h a l l Space Flight C e n t e r Huntsville. 41a b a m a -I b 1 INTRODUCTION At t h e t i m e t h e d e c i s i o n w a s m a d e t o apply a u t o m a t i c techniques t o t h e p r o c e s s of checking out and launching a S a t u r n v e h i c l e , t h e t o t a l o p e r a t i o n w a s u n d e r m a n u a l c o n t r o l . C o n s i d e r a b l e a d v a n c e s have been m a d e i n t h e t r a n s i t i o n f r o m m a n u a l t o c o m p u t e r c o n t r o l . The purpose of t h i s p a p e r i s t o p r e s e n t a projection of the i m p r o v e m e n t s t h a t m u s t be m a d e b e f o r e m a x i m u m benefits c a n be obtained f r o m t h e a u t o m a t i o n e f f o r t . A brief d e s c r i p t i o n i s given of t y p i c a l checkout o p e r a t i o n s and of t h e evolution of h a r d w a r e . With t h i s a s background, a n a n a l y s i s i s m a d e of t h e i m p l e m e n t a t i o n p r o b l e m s e x p e r i e n c e d in a u t o m a t i o n ; and f i n a l l y , f r o m t h i s a n a l y s i s p r o j e c t i o n s a r e d e r i v e d and s t a t e d . CHECKOUT OPER 4TIONS As s t a t e d above, t h i s s e c t i o n p r e s e n t s a brief d e s c r i p t i o n of t h e t e s t i n g o p e r a t i o n . No a t t e m p t i s m a d e t o d e s c r i b e a l l of the i n t r i c a c i e s of t h e t a s k s i n c e t h i s i s not t h e t h e m e of t h e p a p e r . The p u r p o s e i s t o e x p o s e t h e r e a d e r t o the p a r a m e t e r s which m u s t be c o n t r o l l e d and m o n i t o r e d , plus provide a g e n e r a l u n d e r s t a n d i n g of t h e n a t u r e of t h e o p e r a t i o n . T h i s i s n e c e s s a r y f o r the r e a d e r t o u n d e r s t a n d t h e h a r d w a r e r e q u i r e m e n t s and s u b s e q u e n t a n a l y s i s s e c t i o n . F i g u r e 1 i s u s e d t o a i d t h e a c c o m p l i s h m e n t of t h i s objective. It d o e s not r e p r e s e n t a n y s p e c i f i c t e s t p r o g r a m ( s u c h a s post-manufacturing c h e c k o u t , s t a t i c f i r i n g , e t c . ) but p r e s e n t s the g e n e r a l s t r u c t u r e of a l l t e s t o p e r a t i o n s . P r e s e n t e d a r e t h e v a r i o u s s y s t e m s t e s t s which a r e gene r a l l y p e r f o r m e d c o n c u r r e n t l y , followed by t y p i c a l combined s y s t e m s tests. T h e following d i s c u s s i o n w i l l d e s c r i b e t h e t y p e s of s i g n a l s involved a n d g r o s s l y t h e i r a r r a n g e m e n t . �T h e n e t w o r k s a r e u s u a l l y defined a s t h e c i r c u i t r y w h i c h c o n t r o l s , m o n i t o r s , a n d s u p p l i e s power t o t h e v a r i o u s black boxes u s e d i n t h e vehicle. In performing control functions, this c i r c u i t r y usually applies o r r e m o v e s d . c . v o l t a g e t o o r f r o m t h o s e b l a c k boxes a c c o r d i n g t o p a r t i c u l a r s e q u e n c e a n d / o r s e t of l o g i c . In doing s o , i t a c c o m p l i s h e s s u c h o p e r a t i o n s a s ; s t a r t , cutoff a n d s a f i n g , m a l f u n c t i o n d e t e c t i o n , s e p a r a t i o n , d e s t r u c t , e t c . T h e m o n i t o r i n g f u n c t i o n c o n s i s t s of providing high r e s o l u t i o n , r e l i a b l e , r e a l - t i m e i n f o r m a t i o n t o t h e g r o u n d s y s t e m s and personnel. This information, a s with the control functions, i s u s u a l l y i n t h e f o r m of 2 8 v o l t s i g n a l s w h i c h a r e n e i t h e r on o r off. E a c h of t h e c i r c u i t s m u s t be v e r i f i e d t o i n s u r e t h a t e a c h c o m p o n e n t w i l l p e r f o r m i t s intended function without interfering with other c i r c u i t s . D u r i n g t h e t e s t s of t h e o t h e r s y s t e m s , d i f f e r e n t t y p e s of s i g n a l s a r c e n c o u n t e r e d . T h e g u i d a n c e a n d c o n t r o l c h e c k s r e q u i r e being a b l e to apply simulated e r r o r signals to the stabilized nlatform, r a t e gyros, c o n t r o l a c c e l e r o m e t e r s a n d o t h e r e r r o r s e n s i n g d e v i c e s . The r e s p o n s e f r o m these devices m u s t b e m e a s u r e d simultaneously with the application of t h e s t i m u l i t o c h e c k t h e c a l i b r a t i o n . In m o s t c a s e s t h e s e s i g n a l s a r e a n a l o g , c o n s i s t i n g of v a r i o u s v o l t a g e s a n d f r e q u e n c i e s ; c o m m u n i c a t i o n w i t h t h e c o m p u t e r i s v i a a d i g i t a l l i n k , r e p r e s e n t i n g a n o t h e r t y p e of s i g n a l . In i t s v e r i f i c a t i o n v a r i o u s d i a g n o s t i c r o u t i n e s m u s t be p e r f o r m e d , plus v e r i f y i n g t h e i n t e r f a c i n g of t h i s e q u i p m e n t w i t h t h e o t h e r f u n c t i o n a l e l e m e n t s of t h e g u i d a n c e a n d c o n t r o l s y s t e m s . T h i s r e q u i r e s the capability to handle, i n s o m e c a s e s , the s a m e analog p a r a m e t e r s a s previously mentioned and i n other c a s e s , d i s c r e t e signals which o p e r a t e v a r i o u s c o m p o n e n t s on t h e v e h i c l e v i a t h e s w i t c h s e l e c t o r . T e s t i n g of t h e i n s t r u m e n t a t i o n a n d R F ( r a d i o f r e q u e n c y ) s y s t e m s r e p r e s e n t s t i l l a n o t h e r t y p e of o p e r a t i o n . V e r i f i c a t i o n of t h e TM ( t e l e m e n t r y ) p a c k a g e s r e q u i r e s o s c i l l a t o r a d j u s t m e n t , p o w e r output c h e c k s , etc. ; and the R F packages requires frequency interrogation, 4GC checks plus VSWR on a l l a n t e n n a e . As f a r a s t h e p a r a m e t e r s a r e c o n c e r n e d on t h e input t o t h e T M p a c k a g e , t h e y a r e not a n y d i f f e r e n t (with t h e e x c e p t i o n of v i b r a t i o n m e a s u r e m e n t s ) i n t y p e t h a n e n c o u n t e r e d i n t h e o t h e r s y s t e m s . The differences a r e in the acquisition and processing methods T h e p r i m a r y function of t h e i n s t r u m e n t a t i o n s y s t e m i s t o m o n i t o r t h e p e r f o r m a n c e of t h e o t h e r s y s t e m s . T h e r e f o r e , t h e v e r i f i c a t i o n m u s t be a c c o m p l i s h e d d u r i n g t h e t e s t i n g of t h e s e s y s t e m s . C o n s e q u e n t l y , a highly i n t e g r a t e d a n d c o o r d i n a t e d o p e r a t i o n i s n e c e s s a r y . �Testing the mechanical s y s t e m s requires the capability t o control D r e s s u r e t o the v a r i o u s pneumatic and propellant s y s t e m s , verify e n g i n e s , both m e c h a n i c a l l y a n d e l e c t r i c a l l y , e t c . The p a r a m e t e r s i n volved i n s u c h a n o p e r a t i o n r u n t h e g a m u t . An a d d i t i o n a l a t t r i b u t e of t h i s o p e r a t i o n i s s a f e t y , t h u s r e q u i r i n g continuous m o n i t o r i n g of c e r t a i n parameters. In t h e c o m b i n e d s y s t e m s t e s t s , t h e o p e r a t i o n c h a n g e s f r o m p a r a l l e l t o s e r i e s . With e x c e p t i o n of a c t u a l l y loading p r o p e l l a n t s , no new p a r a m e t e r s a r e i n v o l v e d ; h o w e v e r , t h e whole n a t u r e of t h e o p e r a t i o n c h a n g e s . The specific s y s t e m s t e s t s have the p r i m a r y objective t o verify the int e r n a l f u n c t i o n s of e a c h s y s t e m . The p r i m a r y o b j e c t i v e of t h e c o m b i n e d s y s t e m s t e s t s i s t o a s s u r e t h a t t h e r e a r e no i n t e r f a c i n g p r o b l e m s a m o n g t h e s y s t e m s . E a c h of t h e c o m b i n e d s y s t e m s t e s t s h a s d i f f e r e n t o b j e c t i v e s , but t h e c o m m o n a s p e c t i s t h a t a l l of t h e s y s t e m s a r e o p e r a t i n g i n a n itt egrated fashion. This requires that the total operational sequence be p r e - p l a n n e d a n d t h a t e a c h s y s t e m e n g i n e e r h a v e t h e c a p a b i l i t y t o know t h e p e r f o r m a n c e of h i s s y s t e m . MANUAL HARDW ARE REQUIRED T u r n i n g t o t h e GSE r e q u i r e d t o p e r f o r m t h e m a n u a l t e s t i n g o p e r a t i o n , F i g u r e 2 r e p r e s e n t s a typical testing complex. The figure depicts the w a y i n w h i c h t h e G S E i s o r g a n i z e d , by s y s t e m s , a n d t h e v a r i o u s t y p e s of s i g n a l s d e s c r i b e d p r e v i o u s l y . I n g e n e r a l , t h e f i g u r e i s p r e t t y s e l f e x p l a n a t o r y . E a c h t e s t e n g i n e e r c o n t r o l s h i s s y s t e m v i a p a n e l s equipped with switches f o r s t i m u l i a n d m e t e r s and lights for r e s p o n s e monitoring. H o w e v e r , t h e o p e r a t i o n involving t h e i n s t r u m e n t a t i o n s y s t e m m a y r e . q u i r e e l a b o r a t i o n . T o i n s u r e t h e c a l i b r a t i o n of t h e m e a s u r e m e n t s , i t i s f i r s t n e c e s s a r y t o c h e c k f r o m t h e t r a n s d u c e r t h r o u g h t h e s i g n a l conditioni n g , w h i c h i s a c c o m p l i s h e d by obtaining a h a r d w i r e r e c o r d i n g . T h e m e a s u r e m e n t i s then switched to the telemetry s y s t e m and a recording i s o b t a i n e d v i a R F link. T h e s e r e c o r d i n g s a r e t h e n c o m p a r e d t o i n s u r e a c c u r a c i e s of t h e T M s y s t e m . l T h e a n i m a t i o n p o r t i o n of t h e f i g u r e d e p i c t s how t h e t e s t i n g o p e r a t i o n i s coordinated and conducted. E a c h s y s t e m engineer i s responsible for h i s s y s t e m s w i t h t h e t o t a l o p e r a t i o n being d i r e c t e d by a t e s t c o n d u c t o r . REASONS F O R AUTOMATION It m i g h t s e e m a p p r o p r i a t e a n d helpful a t t h i s point t o a s k t h e q u e s t i o n "If t h e h a r d w a r e n e c e s s a r y t o a c c o m p l i s h t h e job i s a v a i l a b l e , why �develop complex digital equipment t o automate the proces s t ' ? The basic r e a s o n s a r e found in the design concept and m i s s i o n r e q u i r e m e n t s of the S a t u r n v e h i c l e s . F r o m the d e s i g n viewpoint, the concept is a staging a p p r o a c h with e a c h s t a g e being developed a t a different location i n t h e United S t a t e s . F r o m a m i s s i o n viewpoint the s a m e basic vehicle m u s t be a b l e t o a c c o m p l i s h varying m i s s i o n s with v a r y i n g launch r a t e s . T o provide the capability t o i n t e g r a t e t h e s e s t a g e s into a launch vehicle a t t h e launch s i t e and provide the n e c e s s a r y m i s s i o n flexibility a n onboard c o m p u t e r s e e m e d t o be the a n s w e r . In addition, the data r e q u i r e m e n t s t o v e r i f y a s t a g e w e r e becoming quite voluminous. T h e r e a r e two c o n s i d e r a t i o n s to this point. F i r s t , i s t k d a t a n e c e s s a r y on a r e a l - t i m e b a s i s during the t e s t i n g operation. Second, i s the d a t a that needs t o be analyzed, but t h i s a n a l y s i s c a n be p e r f o r m e d a f t e r the t e s t i s completed. F i g u r e 2 shows the t e s t engineeF a s t h e m e a n s of accomplishing the data a n a l y s i s i n a r e a l - t i m e situation As t h e s y s t e m s become l a r g e r and m o r e complex, m o r e people a r e involved. This i n c r e a s e s the complexity of the coordination n e c e s s a r y t o a c c o m p l i s h the t e s t i n g operation. 4 c o m p u t e r has the capability to monitor a l l of t h e data points, c o m p a r e the a c c u r a c i e s , i s s u e subs e q u e n t c o m m a n d s , a n d c o o r d i n a t e t h e p e r f o r m a n c e of l a r g e t e s t s than the e n g i n e e r s involved. S i m i l a r l y , t h e magnitude of the off-line data a n a l y s i s t a s k i n c r e a s e d , which a c o m p u t e r c a n p e r f o r m much faster. In the data gathering and p r o c e s s i n g , t h e r e a r e s o m e r e a l advantag e s t o be gained f r o m automation concerning a c c u r a c y and repeatibility. If a t e s t p r o c e d u r e i s c o n v e r t e d t o a n a u t o m a t i c p r o g r a m , t h i s t e s t will be p e r f o r m e d i n t h e s a m e m a n n e r e a c h t i m e i t i s run. Consequently, the d a t a d e s c r i b i n g the p e r f o r m a n c e of the s y s t e m should be r e p e a t a b l e . 4 1 ~ 0 ,i t was planned that the s a m e t e s t p r o g r a m could be p e r f o r m e d a t d i f f e r e n t t e s t l o c a t i o n s , s u c h a s t h e f a c t o r y checkout and s t a t i c t e s t l o c a t i o n s . However, t h i s objective has not m a t e r i a l i z e d t o the d e g r e e initially planned. This l a r g e l y i s a r e s u l t of GSE and s t a g e configuration differences. Another advantage i s t h a t a higher d e g r e e of a c c u r a c y i s obtained through g r e a t e r s e n s i t i v i t y of the m e a s u r i n g d e v i c e s . This i s evidenced i n m e a s u r i n g analog p a r a m e t e r s and i n timing the bi-level s i g n a l s . 4nother advantage of significance i s the s h o r t t i m e r e q u i r e d to p e r f o r m a t e s t provided no a n o m a l i e s o c c u r r e d . This has p a r t i c u l a r payoffs by being a b l e t o p e r f o r m l a t e c h e c k s of a s y s t e m p r i o r t o s t a t i c f i r i n g o r a n a c t u a l launch. 4 �AUTOMATION HARDWARE CCPJCEPT T h e p o s t - m a n u f a c t u r i n g c h e c k o u t of a S a t u r n s t a g e p r o v i d e d t h e f i r s t a p p l i c a t i o n of a u t o m a t i c t e c h n i q u e s a n d a r e s t i l l i n u s e . I n h e r e n t in the application w e r e s o m e c o n s t r a i n t s which proved t o have f a r - r e a c h ing i m p a c t s . C o n s o l i d a t e d a n d r e d u c e d t o t h e b a s i c e l e m e n t s , t h e s e c o n s t r a i n t s w e r e : ( 1 ) no s c h e d u l e i m p a c t t o t h e p r o g r a m , a n d ( 2 ) no l a r g e r e d e s i g n e f f o r t t o t h e s t a g e a n d GSE. T h e f i r s t c o n s t r a i n t m e a n t t h a t t h e a d a p t i o n of a u t o m a t i c e q u i p m e n t t o t h e m a n u a l e q u i p m e n t would b c a c c o m p l i s h e d on a n o - i n t e r f e r e n c e b a s i s . T h e s e c o n d c o n s t r a i n t m e a n t t h a t t h e a u t o m a t i c e q u i p m e n t a n d t e c h n i q u e s would be d e s i g n e d t o i n t e r f a c e w i t h t h e GSE a n d not w i t h t h e v e h i c l e s y s t e m s . F i g u r e 3 d e m o n s t r a t e s t h i s point a n d i s u s e d t o p o r t r a y t h e s y s t e m w h i c h h a s b e e n i m p l e m e n t e d . I t c o n s i s t s of a t h r e e g e n e r a l p u r p o s e c o m p u t e r complex with r e m o t e satellite t e s t stations. 4 p r i m a r y a s s e t of t h i s s y s t e m i s i t s f l e x i b i l i t y p r o v i d e d t h r o u g h t h e u s e of t h r e e individ u a l c o m p u t e r s . T h e c o n s t r a i n t s of no p r o g r a m i m p a c t m a g n i f i e d t h e i m p o r t a n c e of t h i s f l e x i b i l i t y . It a l l o w e d one c o m p u t e r t o be v e r i f y i n g t h e i n t e r f a c e w i t h t h e p e r i p h e r y e q u i p m e n t a n d developing u t i l i t y p r o g r a m s w h i l e t h e o t h e r two c o m p u t e r s c o u l d be v e r i f y i n g t h e t e s t s t a t i o n i n t e r f a c e s and developing t e s t p r o g r a m s . A f t e r t h e v e r i f i c a t i o n of t h e a u t o m a t i o n s y s t e m a n d d u r i n g t h e s t a g e t e s t i n g o p e r a t i o n s , a l l of t h e c o m p u t e r s w e r e u s e d s i m u l t a n e o u s l y only d u r i n g t h e o v e r a l l s y s t e m s t e s t s . C o n s e q u e n t l y , a t l e a s t one c o m p u t e r w a s a v a i l a b l e f o r debugging p r o g r a m s t o be u s e d i n f u t u r e t e s t s . E a c h t e s t s t a t i o n w a s g i v e n t h e c a p a b i l i t y t o a c c e p t a n d output d i s c r e t e a n d a n a l o g s i g n a l s . T h e d e g r e e of c a p a b i l i t y f o r e a c h type d e p e n d e d upon t h e s t a g e s y s t e m f o r w h i c h t h e s t a t i o n w a s d e s i g n e d . Man-machine interfacing with e a c h t e s t station w a s provided through a f l e x o - w r i t e r . T h i s a l l o w e d t h e t e s t e n g i n e e r t o o p e r a t e a l l of t h e i n p u t / o u t p u t c a p a b i l i t y of t h e t e s t s t a t i o n m a n u a l l y . I n a d d i t i o n , t h e e x e c u t i v e p r o g r a m w a s d e s i g n e d t o allow h i m t o c a l l u p p r o g r a m s f r o m t h e c e n t r a l c o m p u t e r c o m p l e x . O n c e a p r o g r a m w a s o n - l i n e , i t could be s i n g l e s t e p p e d o r r u n c o m p l e t e l y a u t o m a t i c . C o m m u n i c a t i o n between the central computer complex and the t e s t stations was via a distribution m a t r i x which allowed any c o m p u t e r t o work with any t e s t station. �As r e f e r e n c e d p r e v i o u s l y , t h e a m o u n t of d a t a w h i c h w a s n e c e s s a r y t o r e c o r d a n d a n a l y z e w a s g e t t i n g unwieldly. T o be a b l e t o handle t h e d i s c r e t e b i - l e v e l t y p e s i g n a l s , a CEE ( d i g i t a l e v e n t s e v a l u a t o r ) w a s developed. T h i s d e v i c e h a s t h e c a p a b i l i t y t o a c c e p t a c h a n g e of s t a g e , r e c o r d t h e t i m e a n d i d e n t i f i c a t i o n a n d output a r e c o r d on t a p e o r p r i n t e r . C a p a b i l i t y i s p r o v i d e d by s o f t w a r e f o r r e a l - t i m e o r off-line e v a l u a t i o n . As c a n be o b s e r v e d by c o m p a r i n g F i g u r e s 2 a n d 3 , s o m e m o d i f i c a t i o n s w e r e m a d e t o t h e GSE t o a l l o w c o n t r o l a n d m o n i t o r i n g of t h e s t a g e s y s t e m s . B e c a u s e of t h e c o n s t r a i n t of no l a r g e r e d e s i g n e f f o r t , t h e m o d i f i c a t i o n s w e r e e n g i n e e r e d u s i n g t h e g u i d e l i n e s of providing a c c e s s t o the existing m a n u a l control and monitoring functions. In the e l e c t r i c a l a r e a s , this w a s relatively e a s y since the s t a g e s have a l w a y s b e e n c o n t r o l l e d a n d m o n i t o r e d by r e m o t e t e c h n i q u e s . T h e r e f o r e , i n t h e g e n e r a l c a s e , i t w a s a m a t t e r of " t e e i n g " t h e s e f u n c t i o n s i n a blockhouse d i s t r i b u t o r a n d c o n n e c t i n g t h e m t o t h e a p p r o p r i a t e t e s t station. A u t o m a t i o n of t h e i n s t r u m e n t a t i o n s y s t e m t e s t i n g o p e r a t i o n r e q u i r e d a s o m e w h a t d i f f e r e n t a p p r o a c h . I n F i g u r e 3 , t h e p r o b l e m of gaining a c c e s s t o r e c o r d t h e m e a s u r e m e n t s b e t w e e n t h e s i g n a l conditioning and t h e T M p a c k a g e w a s a m a t t e r of "teeing" t h e m e a s u r e m e n t a n d c o n n e c t ing t o the r e c o r d e r and Instrumentation T e s t Station. However, t o a c c o m p l i s h t h e c o m p a r i n g of h a r d w i r e r e c o r d i n g w i t h t h e T M r e c o r d r e q u i r e d digitizing the information the T M ground station received. T h i s w a s a c c o m p l i s h e d by d e s i g n i n g e q u i p m e n t t o a c c e p t t h e TM s i g n a l s a t t h e d i s c r i m e n a t o r s and d e c o m m u t a t o r s , digitize t h e s e m e a s u r e m e n t s and i n t e r f a c e t h e m with the Instrumentation T e s t Station. P r o g r a m s w e r e p r o v i d e d t o do t h e c o m p a r i s o n a n d p r i n t t h e r e s u l t s on t h e f l e x o writer. About t h i s t i m e , a n o t h e r m e t h o d of a c c o m p l i s h i n g t h e s a m e t e c h n i q u e s u s i n g o n - b o a r d e q u i p m e n t w a s being d e v e l o p e d . T h i s m e t h o d h a s c o m e t o be known a s DDAS ( D i g i t a l Data A c q u i s i t i o n S y s t e m ) a n d h a s r e p l a c e d t h e e a r l i e r t e c h n i q u e i n m o s t c a s e s . T h e a d v a n t a g e s of converting the m e a s u r e m e n t s t o digital f o r m on the s t a g e i s the reducti o n of n o i s e p r o b l e m s a n d l e s s g r o u n d e q u i p m e n t i s r e q u i r e d . L e s s s u s c e p t i b i l i t y t o n o i s e i s a c h i e v e d by having l e s s w i r e l e n g t h b e t w e e n t h e m e a s u r e m e n t a n d t h e A / D c o n v e r t e r (analog t o d i g i t a l ) . L e s s e q u i p m e n t i s a c h i e v e d by e l i m i n a t i n g a n d / o r r e d u c i n g t h e need f o r g r o u n d recorders. �F i g u r e 3 does not depict one piece of equipment used in the e a r l y phases of automating i n s t r u m e n t a t i o n checkout. This w a s a p r e s s u r e balance s y s t e m u s e d t o a p p l y a known p r e s s u r e s t i m u l i t o the p r e s s u r e t r a n s d u c e r , thus providing a b a s i s f o r c o m p a r i n g t h e r e c o r d i n g taken a t t h e s i g n a l conditioner output. I n c r e a s e d quality and reliability of t h e t r a n s d u c e r and the implementation of t h e R 4CS (Remote Automatic C a l i b r a t i o n S y s t e m ) h a s deleted t h e n e c e s s i t y for t h i s technique. The RACS provide f o r a two-point c a l i b r a t i o n check of the a m p l i f i e r by being a b l e t o apply a known signal a t the high and low end of a n a m p l i f i e r r a n g e . The t r a n s d u c e r provides a t h i r d point by m e a s u r i n g the a m b i e n t conditions of t h e s y s t e m which i t i s monitoring. In t h e m e c h a n i c a l s y s t e m s , much m o r e modification w a s n e c e s s a r y t o obtain c o m p l e t e r e m o t e a u t o m a t i c control. As mentioned previously, the m e c h a n i c a l checkout o p e r a t i o n w a s neither r e m o t e l y o r automatically c o n t r o l l e d . G e n e r a l l y , p r e s s u r e s w e r e s e t up by using hand valves and hand l o a d e r s and w e r e m o n i t o r e d by a l o c a l gauge. To achieve r e m o t e c o n t r o l r e q u i r e d t h e addition of solenoid o r m o t o r d r i v e n l o a d e r s f o r venting loading p r e s s u r e s f o r shut-down, t r a n s d u c e r s t o provide r e a d i n g s a t r e m o t e locations and s o m e s e l f - d i a g n o s t i c capability i n c a s e of a b n o r m a l conditions. Space will not p e r m i t t h e d e s c r i p t i o n of the a u t o m a t i c s y s t e m s t h a t a r e now u s e d i n the S a t u r n I B and S a t u r n V P r o g r a m s . The s y s t e m s now u s e d , with one exception, employ a single c o m p u t e r r a t h e r t h a n a m u l t i - c o m p u t e r a s the c e n t r a l c o m p u t e r complex. In one p a r t i c u l a r application of t h e c e n t r a l c o m p u t e r complex s y s t e m a l l of t h e input/output capability i n c o r p o r a t e d i n the t e s t s t a t i o n h a s been integrated. IMPLEMENTATION ANALYSIS So f a r , this paper has been devoted t o a d e s c r i p t i o n of the testing o p e r a t i o n , the h a r d w a r e and h a r d w a r e changes n e c e s s a r y t o convert t h i s o p e r a t i o n f r o m m a n u a l t o automatic. The next phase will p r e s e n t a n a n a l y s i s of t h e p r o b l e m s e n c o u n t e r e d during t h e implementation phase. T h e s e p r o b l e m s c a n be grouped into t h r e e c a t e g o r i e s : (1) (2) (3) Hardware Software People �T h e r e a d e r w i l l note i m m e d i a t e l y t h a t t h e s e a r e v e r y g e n e r a l c a t e g o r i e s ; t h e r e f o r e , the s p e c i f i c s within m u s t be f r a m e d . Hardware In t h e h a r d w a r e c a t e g o r y , i n c o m p a t i b i l i t y p r o b l e m s w e r e e n c o u n t e r e d within t h e a u t o m a t i o n e q u i p m e n t i t s e l f ; t h e r e w e r e i n c o m patibility p r o b l e m s e n c o u n t e r e d w i t h t h e s i g n a l functions which the e q u i p m e n t w a s d e s i g n e d t o handle. T h e r e w e r e o t h e r p r o b l e m s conc e r n i n g t h e c a p a b i l i t y of the e q u i p m e n t t o m a n a g e t h e o p e r a t i o n a l r e q u i r e m e n t s . T h e s o l u t i o n t o t h e s e p r o b l e m s h a s brought a b o u t a c o n s i d e r a b l : a m o u n t of a d v a n c e s i n h a r d w a r e d e s i g n and t e c h n i q u e s . T h e r e i s a b a s i c s y s t e m p r o b l e m t h a t b e c o m e s evident a f t e r the automation equipment i s interfaced and i s performing a testing o p e r ation. This problem was alluded t o in the discussion concerning the c o n s t r a i n t s i m p o s e d i n t h e i n i t i a l a p p l i c a t i o n of a u t o m a t i c t e c h n i q u e s . It w a s pointed out t h a t t h e r e w a s t o be no m a j o r r e d e s i g n e f f o r t of the v e h i c l e . T h i s r e s u l t e d i n t h e a u t o m a t i o n e q u i p m e n t being i n t e r f a c e d w i t h t h e GSE r a t h e r t h a n t h e s t a g e s y s t e m s . H e r e i n l i e s t h e s y s t e m p r o b l e m . T h e e f f e c t being not a r e d u c t i o n of g r o u n d s u p p o r t equipm e n t ; but i n s t e a d a n a d d i t i o n of a u t o m a t i o n e q u i p m e n t t o p e r f o r m the c o m m u n i c a t i o n a n d i n t e g r a t i o n t a s k t h a t the m a n w a s doing. With t h e c o n c e p t of i n t e r f a c i n g t h e 110 (input-output) of t h e c o m p u t e r t o t h e GSE, t h e GSE i s c o n s i d e r e d t o be t h e d e c i s i o n making d e v i c e . T h e c o m p u t e r i s c o n s i d e r e d only a m e a n s of c o m m u n i c a t i n g the s t a t u s of t h e GSE a n d v e h i c l e t o t h e e n g i n e e r s . T h i s c o n c e p t f a i l s t o u s e one of t h e s t r o n g a s s e t s of t h e c o m p u t e r ; t h i s i s i t s c a p a b i l i t y t o g a t h e r d a t a a n d m a k e s u b s e q u e n t d e c i s i o n s . A continuance of t h i s philosophy w i l l i n c r e a s e t h e s i z e a n d c o m p l e x i t y of t h e h a r d w a r e and s o f t w a r e system. Another way of d e s c r i b i n g t h e s a m e p r o b l e m i s by taking a r a t h e r a n t h r o p o m o r p h i c view of t h e v e h i c l e a n d GSE. T h e method of c o m m u n i c a t i o n of a c o m p u t e r i s a d i g i t a l language. With the e x c e p t i o n of t h e o n - b o a r d c o m p u t e r s a n d t h e DDAS (which c o n c e r n s only r e s p o n s e s ) t h e v e h i c l e u n d e r s t a n d s only d i s c r e t e a n d a n a l o g language. T h e r e f o r e , t h e m a j o r p u r p o s e of t h e e l e c t r i c a l GSE i s t o be a n i n t e r p r e t e r between t h e c o m p u t e r a n d the v e h i c l e . I t b e c o m e s a p p a r e n t t h e n t h a t s t e p s need t o be t a k e n t o g e t t h e v e h i c l e t o c o m m u n i c a t e i n a language m o r e c l o s e l y a l i g n e d w i t h t h e c o m p u t e r language. T h e two e x c e p t i o n s r e f e r r e d t o �above r e p r e s e n t s t e p s i n this d i r e c t i o n s i n c e both communicate via digital links. By expanding t h e i r u s e provides the key f o r a c c o m p l i s h ing the additional s t e p s n e c e s s a r y . The w r i t e r w i s h e s t o make v e r y e x p l i c i t , a t t h i s point, that the above logic i s u s e d t o e s t a b l i s h a longr a n g e goal. T h e r e a r e many i n c r e m e n t a l s t e p s n e c e s s a r y before that goal c a n be r e a c h e d . Also, t h e r e a r e many t r a d e - o f f s concerning complexity which m u s t be m a d e between the vehicle and t h e ground equipment. T o r e a c h this goal, t h e following actions need t o be taken: (1) I n c r e a s e d r e l i a n c e on DDAS. r e l i a b i l i t y and handling techniques . This will r e q u i r e i m p r o v e d (2) R e a s s e s s t h e balance of complexity between the vehicle and GSE. In o r d e r t o achieve l a r g e reductions of e l e c t r i c a l GSE, i t would be profitable t o allow m o r e complexity on-board the vehicle. ( 3 ) E l i m i n a t e the need f o r t o t a l checkout capability a t the launch o p e r a t i o n s . T h i s c a n be achieved by delivering t o the launch o p e r a t i o n s totally configured and v e r i f i e d s t a g e s . (4) Review the interlocking r e q u i r e m e n t s , using t h e guiclel i n e of allowing t h e c o m p u t e r t o m a k e t h e decision. (5) Develop m e a n s of controlling vehicle s y s t e m s through the u s e of o n - b o a r d techniques a n d / o r expanded u s e of p r e s e n t c a p a b i l i t i e s . By being a b l e t o c o n t r o l t h e vehicles through u s e of on-board s y s t e m s , a r e d u c t i o n i n t h e i n t e r f a c e points between the vehicle and GSE i s gained. If the n u m b e r of the i n t e r f a c e points i s r e d u c e d , two i m p a c t s a r e a consequence. F i r s t , t h e r e i s a g e n e r a l reduction of GSE, s i m p l y bec a u s e t h e r e a r e l e s s functions t o be handled. Second, t h e r e i s l e s s possibility of a change i n the vehicle causing a subsequent change i n t h e GSE. An e x a m p l e of this i s i n the way the DDAS p e r f o r m s . S e v e r a l hundred m e a s u r e m e n t s m a y input t o the DDAS, but the output i s a single wave t r a i n . T h e r e f o r e , many m e a s u r e m e n t changes c a n be m a d e with the only e f f e c t t o t h e GSE being a change t o the m e a s u r e m e n t a d d r e s s in the CDAS wave t r a i n . This type of change c a n be accepted by a change in the s o f t w a r e . Software Providing a s o f t w a r e s y s t e m to i m p l e m e n t the automation of thc, checkout and launch o p e r a t i o n s h a s been and continues to be one of the m o s t challenging a s p e c t s of the automation endeavor. �T h e d i s c u s s i o n c o n c e r n i n g t h e n a t u r e of t h e t e s t i n g o p e r a t i o n pointed out t h e v a r i e t y of s i g n a l s involved a n d t h e d i f f e r e n t t y p e s of t e s t s c o n d u c t e d . T o c r e a t e a s o f t w a r e s y s t e m t o m a n a g e t h i s t y p e of o p e r a t i o n r e q u i r e s a t r e m e n d o u s a m o u n t of c a p a b i l i t y a n d f l e x i b i l i t y . I n doing a n a n a l y s i s of t h e d i f f i c u l t i e s t h a t w e r e e n c o u n t e r e d , e a c h s e e m e d t o be r o o t e d t o a v e r y b a s i c a n d f u n d a m e n t a l point; t h a t of being a b l e t o d e s c r i b e a l l of t h e r e q u i r e m e n t s of t h e job. Of c o u r s e , t h i s i s a n e s s e n t i a l i n g r e d i e n t i n a n y t a s k . But, i t r e a f f i r m s t h e point t h a t t h e b e s t s p e n t t i m e i n a n y new e n d e a v o r i s t h a t s p e n t i n d e s c r i b i n g t h e t a s k a n d planning i t s i m p l e m e n t a t i o n . T h e p r o b l e m s t h e t e s t e n g i n e e r e n c o u n t e r e d i n providing s y s t e m s t e s t r e q u i r e m e n t s t o t h e p r o g r a m m e r w e r e d i r e c t m a n i f e s t a t i o n s of t h e a b o v e point. P r i o r t o a u t o m a t i o n , t h e e n g i n e e r h a d n e v e r b e e n r e q u i r e d t o d e s c r i b e i n h i s t e s t p r o c e d u r e s a l l of t h e s t e p s , w i t h t h e e x p e c t e d r e s p o n s e s a n d l i m i t s , t o t h e d e t a i l r e q u i r e d by a c o m p u t e r p r o g r a m . O t h e r d i f f i c u l t i e s w e r e e n c o u n t e r e d i n d e t e r m i n i n g t h e a m o u n t of c a p a b i l i t y and f l e x i b i l i t y r e q u i r e d i n t h e e x e c u t i v e p r o g r a m . I n o r d e r t o d e v e l o p a n e x e c u t i v e p r o g r a m , d e c i s i o n s h a v e t o be m a d e c o n c e r n ing m a n - m a c h i n e r e l a t i o n s h i p s , o n - l i n e o r off-line c o m p i l a t i o n , m e m o r y c a p a b i l i t y a n d i n p u t / o u t p u t r e q u i r e m e n t s t o n a m e a few. T h e s e d e c i s i o n s m u s t be m a d e a s e a r l y a s p o s s i b l e s i n c e c h a n g e s t o t h e s e i t e m s w i l l cause m a j o r impact to the executive p r o g r a m development. The language the t e s t engineer should u s e i n writing the t e s t i s p r o b a b l y t h e m o s t c o m p l e x a n d c o n t r o v e r s i a l i s s u e . P a r t of t h e d i f f e r e n c e of opinion i s a r e s u l t of t h e t y p e of s y s t e m being a u t o m a t e d . F o r example, to monitor the instrumentation s y s t e m m a y require a p r o g r a m t o c o n t i n u o u s l y s c a n a g r o u p of m e a s u r e m e n t s . T h i s r e q u i r e s a c o m p l e t e l y d i f f e r e n t t y p e of p r o g r a m t h a n one t o c h e c k o u t t h e cutoff circuitry. The f o r m e r c a s e requires a p r o g r a m t o perform a monitoring function continuously with v e r y little man-machine interfacing. A machine language p r o g r a m i s probably best suited f o r t h e s e needs. T o p e r f o r m a c h e c k of t h e cutoff r e q u i r e s i s s u i n g h i - l e v e l s i g n a l s a n d m o n i t o r i n g f o r c o r r e c t r e s p o n s e s on a s t e p by s t e p b a s i s . T h e r e i s m o r e man-machine interfacing concerning display requirements, c a p a b i l i t y t o c h a n g e t h e c o u r s e of t h e t e s t and s a f e t y c o n d i t i o n s . A m a c h i n e l a n g u a g e p r o g r a m d o e s n ' t p r o v i d e t h e f l e x i b i l i t y , plus t h e t e s t e n g i n e e r l o s e s h i s knowledge of t h e p r o g r a m i n m a c h i n e l a n g u a g e d o c u mentation. 10 �It i s t h e w r i t e r s opinion t h a t t h e s e a r c h f o r a c o m m o n l a n g u a g e (defined a s one l a n g u a g e i n w h i c h a l l t e s t p r o g r a m s a r e w r i t t e n ) i s t h e w r o n g a p p r o a c h . T h e w r i t e r f e e l s t h a t t h e l a n g u a g e u s e d should be d e t e r m i n e d by s u c h c r i t e r i a a s : ( 1 ) t h e n u m b e r of d e c i s i o n s t h e e n g i n e e r s m a y h a v e t o m a k e d u r i n g t h e o p e r a t i o n , (2) t h e r e p e t i v e n e s s of t h e o p e r a t i o n , ( 3 ) t h e s a f e t y c o n s i d e r a t i o n s , (4) t h e d i s p l a y r e q u i r e m e n t s , e t c . All of t h e a b o v e c r i t e r i a a r e c o n c e r n e d w i t h d e t e r m i n ing t h e t y p e of o p e r a t i o n t h a t i s t o be p e r f o r m e d . T h i s i s r e a l l y t h e k e y in d e t e r m i n i n g the language best suited f o r the t e s t p r o g r a m . A language f o r p e r f o r m i n g c o m b i n e d s y s t e m s t e s t s c a n be d e v e l o p e d w h i c h XT i l l c o n t r o l t h e t o t a l o p e r a t i o n a n d a l s o allow t h e a p p r o p r i a t e s u b l a n g u a g e t o be u s e d . Of t h e c r i t e r i a u s e d t o d e v e l o p a s o f t w a r e l a n g u a g e , b e i n g c a p a b l e of a c c e p t i n g c h a n g e s i s c l o s e t o being t h e m o s t i m p o r t a n t . The S a t u r n h a r d w a r e (vehicle and GSE) w e r e designed with m i s s i o n flexibility in mind. Mission flexibility o r a n y flexibility f o r that m a t t e r i s synonymous w i t h c h a n g e s . T h e r e f o r e , a s u s t a i n e d l e v e l of c h a n g e s c a n be e x p e c t e d f o r t h e d u r a t i o n of t h e p r o g r a m . T h e c h a l l e n g e i s t o d e s i g n h a r d w a r e and s o f t w a r e s y s t e m s that will a c c e p t changes with m i n i m u m impact. I m p a c t i n t w o w a y s : (1) t u r n a r o u n d t i m e a n d ( 2 ) t o t a l c o s t ( d o c u m e n t ation, time, manpower). S o f t w a r e s y s t e m s m u s t be v e r i f i e d p r i o r t o t h e i r u s e i n t h e o n - l i n e hardware system. The techniques used for the verification activities m u s t be planned e a r l y . T h e r e a r e m a n y c o s t v s . d e g r e e of v e r i f i c a t i o n t r a d e - o f f s t h a t m u s t be m a d e . T h a t i s , f o r a g i v e n p r o g r a m t h e r e i s a r a n g e of v e r i f i c a t i o n t e c h n i q u e s t h a t c a n be u s e d . T h e y r a n g e f r o m using another software p r o g r a m t o using duplicate h a r d w a r e . Running t h e p r o g r a m o n d u p l i c a t e h a r d w a r e w i l l p r o d u c e t h e m a x i m u m c o n f i d e n c e t h a t t h e g i v e n p r o g r a m i s v e r i f i e d . But, i n g e n e r a l , i t i s a l s o t h e m o s t e x p e n s i v e . F o r t h e v e r i f i c a t i o n of a t o t a l s o f t n a r e s y s t e m t h i s t e c h n i q u e i s n e c e s s a r y . F o r c o m p o n e n t s of t h e s y s t e m a l e s s e r d e g r e e of c o n f i d e n c e c a n p o s s i b l y be a c c e p t e d a n d s u b s e q u e n t l y a l e s s c o s t l y m e t h o d u s e d . What m e t h o d i s u s e d s h o u l d be planned c o n c u r r e n t l y w i t h t h e i n i t i a l d e s i g n of t h e s y s t e m . T h e n e c e s s i t y f o r t h i s i s q u i t e obvious b e c a u s e of t h e t i m e r e q u i r e d t o d e v e l o p t h e v e r i f i c a t i o n p r o g r a m s a n d / o r h a r d w a r e . 4 1 ~ 0 ,a n y c h a n g e s i n plans f r o m a n o r i g i n a l v e r i f i cation concept will cause serious schedule impacts. P r o b a b l y t h e g r e a t e s t m i s c a l c u l a t i o n i n t h e g e n e r a t i o n of a s o f t w a r e s y s t e m w a s t h e t i m e r e q u i r e d . T h e difficulty e n c o u n t e r e d i n t h e �g e n e r a t i o n of the s y s t e m s r e q u i r e m e n t s w a s a contributor t o this t i m e . Independent of this i s the t i m e r e q u i r e d t o c r e a t e , document and v e r i f y a p r o g r a m . P r e v i o u s t o automation the t e s t p r o c e d u r e s w e r e g e n e r a t e d f r o m s y s t e m s r e q u i r e m e n t s , but they could be g e n e r a t e d s h o r t l y p r i o r to running the t e s t . With t h e advent of m o r e complex s y s t e m s and automation t h i s i s no l o n g e r possible. The optimum solution would be to develop a l l of t h e h a r d w a r e e a r l y enough t o allow adequate t i m e f o r s o f t w a r e development. T h i s optimum solution cannot be obtained i n a c o n c u r r e n t p r o g r a m s o techniques m u s t be developed to t r a n s f e r s y s t e m s r e q u i r e m e n t s t o s o f t w a r e p e r s o n n e l c o n c u r r e n t with h a r d w a r e development. E x p e r i e n c e t o date h a s brought the r e a l i z a t i o n that a t o t a l softw a r e s y s t e m h a s t o be developed i n t h e s a m e m a n n e r a s a h a r d w a r e s y s t e m . F i g u r e 4 depicts a software s y s t e m which i s r e p r e s e n t a t i v e of a type t h a t i s n e c e s s a r y f o r the launch o p e r a t i o n s . The m a j o r decisions c o n c e r n i n g t h e components of t h i s s y s t e m have been d i s c u s s e d above. Once t h e s e d e c i s i o n s have been r e a c h e d and the r e l a t i o n s h i p among the components e s t a b l i s h e d , they should c o m e under a configuration management s c h e m e . T h i s will i n s u r e the c o n t r o l of any i n t e r f a c e impacting c h a n g e s . A s e r i o u s d e t e r e n t t o a n automation effort i s t h e lack of u n d e r standing of the c a p a b i l i t i e s and limitations of the s o f t w a r e s y s t e m s . Putting the s o f t w a r e s y s t e m u n d e r a configurationmanagement s c h e m e enhances i t s understanding, because it f o r c e s the s o f t w a r e t o be t r e a t e d a s a s y s t e m with a l l of t h e accompanying documentation. To f u r t h e r a c c e l e r a t e the understanding p r o c e s s t r a i n i n g s e s s i o n s should be conducted explaining t h e design and o p e r a t i o n of the s y s t e m . People L a s t , but m o s t i m p o r t a n t i s t h e people problem. This c a t e g o r y i s probably t h e m o s t complex a s w e l l a s being the m o s t i m p o r t a n t . The w r i t e r i s not s u r e that t h e r e a r e any distinct c h a r a c t e r i s t i c s t h a t can be d e s c r i b e d i n a n explicit, independent fashion. However, t h e r e a r e a couple which s e e m t o be basic and c a n be d e s c r i b e d . F i r s t , t h e r e i s i n a n y new endeavor a knowledge-time p a r a m e t e r . That i s , a t t h e initiation of a n activity t h e r e i s a lack of knowledge of how that a c t i v i t y c a n be a c c o m p l i s h e d , but a s t i m e proceeds this knowledge b e c o m e s a v a i l a b l e . The p r o b l e m i s t o develop the communication methods ( i n t e r m s of organization and information t r a n s f e r ) t o apply t h i s knowledge effectively t o a l l r e q u i r ing a c t i v i t i e s . In the c a s e of automating �S a t u r n I s t a g e t e s t i n g , t h e r e w a s a n u n d e r s t a n d i n g of t h e c h e c k o u t o p e r a t i o n a s i t w a s being p e r f o r m e d m a n u a l l y . T h e r e w a s not a t h o r o u g h u n d e r s t a n d i n g of e a c h h a r d w a r e , s o f t w a r e a n d o p e r a t i o n r e q u i r e m e n t , n o r o r how t h e s e r e q u i r e m e n t s s h o u l d be fulfilled t o a c h i e v e t h e a u t o m a t i o n job. A s s t a t e d a b o v e , t h e r e i s nothing unique a b o u t t h i s s i t u a t i o n . I t a p p l i e s t o a n y new e f f o r t . T h e a s p e c t i n t h e S a t u r n p r o g r a m which m a k e s this m o r e impacting i s the time element. By e x a m i n i n g t h e k n o w l e d g e - t i m e r e l a t i o n s h i p d e s c r i b e d i n F i g u r e 5 i t c a n be s e e n t h a t t h e a u t o m a t i o n s y s t e m c o n c e p t , w h i c h w a s t o s e t t h e pace f o r the S a t u r n I B and V p r o g r a m s , w a s f o r m e d p r i m a r i l y f r o m t h e a c c u m u l a t e d e x p e r i e n c e of only one S a t u r n s t a g e . B e f o r e t h e f u l l c o m p l i m e n t of e q u i p m e n t w a s o p e r a t i o n a l a y e a r a n d a half w a s c o n s u m e d . A s o n e m i g h t e x p e c t , knowledge of how t o d o t h e job a c c u m u l a t e d d u r i n g t h a t t i m e c a u s i n g h a r d w a r e , s o f t w a r e and o r g a n izational changes. T o t a k e this relationship and expand i t over the total S a t u r n I B and V p r o g r a m s , t h e p r o b l e m i s g r e a t l y i n c r e a s e d . It c a n be s e e n f r o m F i g u r e 5 t h a t t h e i n i t i a l c o n c e p t s w e r e being d e v e l o p e d t o p e r f o r m factory checkout, static testing and launch operations - engrossing nine d i f f e r e n t l o c a t i o n s , f i v e s t a g e c o n t r a c t o r s , a n d two NASA C e n t e r s . Very little actual experience, i n proportion to the total program, exi s t e d a t t h a t t i m e . I m p l e m e n t a t i o n of t h e s e c o n c e p t s r e q u i r e d a p p r o x i m a t e l y t h r e e y e a r s . During t h e s e t h r e e y e a r s much experience w a s gained, thus considerably a l t e r i n g the concepts that w e r e f i r s t applied. The second characteristic concerns the attitude toward automating the testing operations. Unfavorable attitudes concerning automation h a v e g e n e r a l l y r e s u l t e d f r o m a l a c k of u n d e r s t a n d i n g of t h e long r a n g e n e e d s a n d b e n e f i t s . T h e s e a t t i t u d e s involved, of c o u r s e , v a r y w i t h i n t h e knowledge-tim:: r e l a t i o n s h i p . I n t h e S a t u r n - A p ~ l l op r o g r a v t h r e e o r four y e a r s a r e required for the launch site personnel t o acquire the s a m e a m o u n t of e x p e r i e n c e a s t h o s e involved i n t h e i n i t i a l d e s i g n and c h e c k o u t o p e r a t i o n s . F u r t h e r , t h i s t i m e i n v o l v e s t h o u s a n d s of people w i t h d i f f e r e n t d i s c i p l i n e s a n d b a c k g r o u n d s . T h e r e f o r e , if t h e l a s t o p e r a t i o n i s t o t a k e a d v a n t a g e of t h e e x p e r i e n c e a n d knowledge g a i n e d p r e v i o u s l y , t h e p r o c e s s of a c c u m u l a t i n g a n d c o m m u n i c a t i n g t h i s e x p e r i e n c e m u s t be a c c e l e r a t e d . �PROJECTIONS AND CONCLUSIONS B e f o r e t h e m a x i m u m benefits c a n be r e a p e d f r o m a u t o m a t i c t e c h niques s e v e r a l a d v a n c e s need t o be m a d e . The f i r s t a n d f o r e m o s t a r e i n t h e people c a t e g o r y . F i r s t of a l l , g o a l s need t o be e s t a b l i s h e d and p r o c l a i m e d . T h e s e g o a l s m u s t be i n t e r m s of f u t u r e conditions f o r which a u t o m a t i c t e c h niques a r e t h e only a n s w e r . In t h e S a t u r n p r o g r a m , g r o u p s of people have r e s i s t e d a u t o m a t i o n on t h e b a s i s t h a t the i m m e d i a t e job, with w h i c h they w e r e c o n c e r n e d , could be done b e t t e r t h e old way. The l o n g e r r a n g e needs should be d e s c r i b e d and explained. A r e c e n t s u r v e y of t h e S a t u r n - A p o l l o P r o g r a m d i s c l o s e d that t h e only functions t h a t h a d n ' t been a u t o m a t e d , a t one location o r a n o t h e r , w e r e l e a k c h e c k s , a m p l i f i e r c a l i b r a t i o n and s o m e monitoring of c r i t i c a l functions. Of t h e s e , i t would be a w a s t e of money t o a u t o m a t e l e a k c h e c k s and s o f t w a r e techniques have been developed t o e l i m i n a t e t h e need f o r a m p l i f i e r c a l i b r a t i o n . S o t h e p r o b l e m i s not technology, but u n d e r standing a n d a t t i t u d e s . T r a i n i n g i s a n a c t i v i t y t h a t n e e d s t o be e x p l o r e d . It i s probably t h e only way i n which t h e l e a r n i n g c u r v e c a n be i m p r o v e d . As d i s c u s s e d p r e v i o u s l y , t h i s i s a v e r y s e r i o u s a s p e c t i n the S a t u r n - A p o l l o p r o g r a m w i t h i t s t i m e s p a n between t h e beginning a n d the end of the t e s t i n g o p e r a t i o n . A l s o , t r a i n i n g c a n be u s e d t o e r a s e a t t i t u d e p r o b l e m s . In t h e h a r d w a r e a r e a s e v e r y s t e p which w i l l allow the vehicle t o be m o r e autonomous should be t a k e n . T h i s w i l l have the effects of r e d u c ing t h e GSE and r e l i e v i n g s o m e of the s o f t w a r e b u r d e n s . To i t e r a t e s o m e of t h e points d i s c u s s e d p r e v i o u s l y , t h e review of interlocking r e q u i r e m e n t s , d e v e l o p m e n t of g r e a t e r r e l i a n c e on DDAS and developm e n t of o n - b o a r d s y s t e m s provide t h e g r e a t e s t potential. B e f o r e the l a t t e r c a n be i m p l e m e n t e d i n t h e m a i n s t r e a m , t e s t a r e a s need t o be provided t o d e v e l o p t h e c h a n g e s . T h i s would a l s o allow t h e p e r s o n n e l t o gain confidence u n d e r r e a l i s t i c conditions, thus aiding t h e i m p l e m e n t ation process. The m a j o r point t h a t n e e d s t o be m a d e i n the s o f t w a r e a r e a i s t h a t i t needs t o be t r e a t e d a s a s y s t e m . Also, i t should be t r e a t e d on an e q u a l b a s i s a s t h e h a r d w a r e . In t h e S a t u r n - A p o l l o P r o g r a m t h i s m e a n s �a t r i a n g u l a r s i t u a t i o n of v e h i c l e , G S E and s o f t w a r e . No change should bc m a d e t o one without c o n s i d e r i n g t h e effect of the other. T o i m p l e m e n t t h i s r e q u i r e s t h a t t h e r e be c o n c u r r e n c y among a l l t h r e e f r o m t h e initial concept t h r o u g h the l a s t launching. Of c o u r s e , t h i s adds complexity t o t h e t o t a l p r o g r a m , but not n e a r a s much a s would be i f this w a s not recognized. - P r o j e c t i n g outside t h e t h e m e of t h i s p a p e r , t h e r e i s one l a s t point t h a t should be e x a m i n e d . T h a t i s t h a t t h e checkout and launch i s only one f a c e t of t h e Saturn-Apollo P r o g r a m . Since they a r e the l a s t a c t i v i t i e s a l l o t h e r a c t i v i t i e s s u p p o r t t h e m . T h e r e f o r e , if f a s t e r , m o r e effective techniques a r e applied t o t h e s e a c t i v i t i e s t h e s a m e techniques need t o be applied t o t h e supporting a c t i v i t i e s . An e x a m p l e of t h i s i s i n a t e s t p r o g r a m which s e n d s a s t i m u l i t o the vehicle t h e n i n t e r r o g a t e s a d a t a t a p e f o r the p r o p e r r e s p o n s e d a t a . The d a t a t a p e i s t o be supplied by e n g i n e e r i n g containing a l l of the p a r a m e t e r s and t h e i r l i m i t s . Howe v e r , if e n g i n e e r i n g i s n ' t g e a r e d t o s u p p o r t t h i s type of o p e r a t i o n , the d a t a t a p e w i l l n e v e r be a v a i l a b l e on s c h e d u l e nor w i l l change capability e x i s t . T h i s s o r t of supporting r e q u i r e m e n t s r e p r e s e n t s a whole field t h a t m u s t be e x p l o r e d and i n t e g r a t e d into t h e t o t a l job. �W I - = w = > C3 ��INSTRUMENTATION TEST STATION PERIPHERY EQUIP TEST STATION RELAY LOGIC ANALOG GEN FIGURE 3 AUTOMATED CHECttOUT OPERATI ON �MAN-MACH INE FIGURE 4 SOFTWARE SYSTEM IN PUT-OUT PUT �DEFINITION O F DEFINITION 0 FIGURE 5 � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000063 Title A name given to the resource "Analysis and Projections of Space Vehicle Automatic Checkout and Launch." Creator An entity primarily responsible for making the resource Vedane, C. R. George C. Marshall Space Flight Center Date A point or period of time associated with an event in the lifecycle of the resource 1966-10-01 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn project (U.S.) Automatic test equipment Rockets (Aeronautics)--Launching Space vehicle checkout program Launching Type The nature or genre of the resource Reports Text Source A related resource from which the described resource is derived Saturn V Collection Box 19, Folder 17 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000051_000074 https://digitalprojects.uah.edu/files/original/76/3317/loc_burw_-113_114.pdf d94db60196b2bc3134f24a35b8f62e47 Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context Burwell Family Collection Title A name given to the resource Burwell Family Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/145" target="_blank" rel="noreferrer noopener">View the Burwell Family Collection finding aid in ArchivesSpace</a> Description An account of the resource <a href="http://libarchstor2.uah.edu/digitalcollections/items/show/3332" target="_blank" rel="noreferrer noopener">View Edwin D. Burwell's World War II service timeline, 1943-1944</a> <a href="http://libarchstor2.uah.edu/digitalcollections/items/show/3333" target="_blank" rel="noreferrer noopener">View Edwin D. Burwell's World War II service timeline, 1944-1945</a> Provenance A statement of any changes in ownership and custody of the resource since its creation that are significant for its authenticity, integrity, and interpretation. The statement may include a description of any changes successive custodians made to the resource. Materials donated and digitized by Dudley Burwell Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context loc_burw_000113_000114 Title A name given to the resource "Annex #1 to accompany March Order No. 1". Description An account of the resource This annex discusses the schedules, vehicle use, and uniforms for March Order Number 1. Creator An entity primarily responsible for making the resource Phillips, Thomas M. Date A point or period of time associated with an event in the lifecycle of the resource 7/20/1949 Temporal Coverage Temporal characteristics of the resource. 1940-1947 Subject The topic of the resource Alabama. Army National Guard United States. Army. Engineer Combat Group, 1169th Fort Benning (Ga.) Type The nature or genre of the resource Orders (military records) Text Source A related resource from which the described resource is derived Burwell Family Collection University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource loc_burw_2021_02 https://digitalprojects.uah.edu/files/original/76/3318/loc_burw_-115_119.pdf c8dbd8173b90e5f60bd158db930bef7a Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context Burwell Family Collection Title A name given to the resource Burwell Family Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/145" target="_blank" rel="noreferrer noopener">View the Burwell Family Collection finding aid in ArchivesSpace</a> Description An account of the resource <a href="http://libarchstor2.uah.edu/digitalcollections/items/show/3332" target="_blank" rel="noreferrer noopener">View Edwin D. Burwell's World War II service timeline, 1943-1944</a> <a href="http://libarchstor2.uah.edu/digitalcollections/items/show/3333" target="_blank" rel="noreferrer noopener">View Edwin D. Burwell's World War II service timeline, 1944-1945</a> Provenance A statement of any changes in ownership and custody of the resource since its creation that are significant for its authenticity, integrity, and interpretation. The statement may include a description of any changes successive custodians made to the resource. Materials donated and digitized by Dudley Burwell Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context loc_burw_000115, loc_burw_000119 Title A name given to the resource "Annex No. 2-March Tables". Description An account of the resource These tables show March Units Numbers one through four with their miles, time, and units. Date A point or period of time associated with an event in the lifecycle of the resource 7/18/1949 Temporal Coverage Temporal characteristics of the resource. 1940-1948 Subject The topic of the resource Alabama. Army National Guard United States. Army. Engineer Combat Group, 1169th Fort Benning (Ga.) Type The nature or genre of the resource Charts Text Source A related resource from which the described resource is derived Burwell Family Collection University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource loc_burw_2021_02 https://digitalprojects.uah.edu/files/original/20/10569/Satannprorep_030408114318.pdf 80981e36b427a0f066c60b2b154062d4 Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context Satannprorep_030408114318.pdf spc_stnv_000681 Title A name given to the resource "Annual progress report :1966-1967." Description An account of the resource The Annual Progress Report from July 1st, 1966 through June 30thm 1967. Creator An entity primarily responsible for making the resource The Boeing Company Launch Systems Branch, Space Division Date A point or period of time associated with an event in the lifecycle of the resource 1967-07-28 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn launch vehicles Saturn S-1C stage Project management Type The nature or genre of the resource Text Progress Reports Source A related resource from which the described resource is derived Saturn V Collection University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000675_000699 https://digitalprojects.uah.edu/files/original/20/1151/spc_stnv_000067.pdf 6d546011779bd6bc44167875ef38a8c8 PDF Text Text SATURN MISTORY DO~"llj--~ Univer"h/ OF Aigbama R~~catch Instikg '"t0.y of Science E bChnD,ogy Dak-- THE I ~ 1 I REPORT L OF THE ! --_------- Doc 'OW --- ---_ �..................... ........................... .............................. I I To Our Stockholders 2 The Foundaflotl 4 Mission Suppart ........................ 4 bearch 6 EIechnigs ............................. 7 Infomation Sciences .18 Structural and Mechanid Systems ....... .19 Architecture and Facilities Engineering ... .21 ................... t h e Future ..............................22 .............. ................... Brown Engineering Facilities .23 Officers and Directors .24 Financial Information ........... Center Pages ............. ............. ........ Cash Wow per share (I). . . . . . . . . Dividends paid . . . . . . . . . . . Total daties and wages . . . . . . . . Net addhiom to buildings, leasehold irnprovements,and equipment . . . . . Net J e a . Net h o m e Net income per share (1) ........ Total sbckhoIders' equity Wotking capital Number of stockholders of remrd Number of employees ........... ..... ......... (I Computed ) on total shares outstandng at close of year 1965 (2) Restated for pooling of interest Received long-term mission support contracts. Built large electronic ground support systems for Saturn program. Acquired Electro-Mechanisms, Inc., a New England electronics manufacturer. Began construction on electronics manufacturing plant at Lewis burg, Tennessee. Established Information Sciences, Inc., in key southeastern cities. De ;EMan fhe wmvw we the SIX a m of sc&vfiy wrrenNy being pursW by Brown Enghee'ring. The subject of' each prcture Is shown w i n in$@ ,the repart t a g h e r with an expkna#Ofl eaphon. �TO OUR STOCKHOLDERS The year 1965 marked an important 12 months far Brown Engineering Company. I n c ~ a s e dsales and earnings were accompanid by other significant events that promise to profoundly affect Brawn's future. For the fgth straight year, the corn pany's safes and earnings Increased over those of the previous 12 months. Sales in 1965 tabled $45,302,418. Net earnings, reachjng the $1 million mark for the fiat time, were $1,134,484, ar This compares with earnings d $924,641, or $1.24 per share, in 1954. $1.52por share. safes of $42,3W,754and Long-term contracts having a poten- In addition to his res 6ibltEties as pfesident and chafrrnan of the at emwe EngInesring Company, Milton K. Cummfngs 1s act/%?in community, state, and natfonal affaffs. �tial value of more than $1M million were awarded the company to provide technical suppart ta the National Aeronautics and Space Administration's George C. Marshall Space Flight Center. The latest awards replaced a m m ber of short-term contracts Brown held with this key NASA installation, and offered the company a solid eeonornic base far the next five years. Brown expanded its markets and capabilities, especially in electronics and information systems, through smaller firms as subsidiaries, new equipment, and facilities. Brown acquired Electro- Mechanisms, Inc., a New EngEahd elec- 3,mO employees, highest employment tronics firm, and established Infarma- in the company's history, and locations tion Sciences, I nc., in Atlanta, Georgia, in Jx states. We believe the events of to prov'rde management and computer "165 will strongly influence the future services. In addition, the company en- success of Brown, Our long-term contered an option to purchase T ram-Data, tracts, along with our expanded mpaInc,, a Huntsville electronics firm. bilities and markets, give us a solid Construction was begun in 1965 on a foundation for growth. manufacturing plant at tewisburg, TenWe are grateful to the many permns nessee, to house a part of the com- - customers, stockholders, and empany's growing electronics operations, ployees - who made 1965 s ~ & a sigand a highly advanced computer was nificant period in Brown's history. Their installed in Brown's data pracesslng continuing interests in our company give us every reason to look to the fulaboratory at Huntsville. At year's end, Brown had more than ture with great confidence. Milton K. Cumrnings Chairman and president ��space and defense deeply involved Brown in programs of the National Aeronautics nnd Space Administration and the Army during 4965. The company made significant contributions to these agencies toward the development of large space boosters for space expIoration defense. and modern missiles for In '1965, Brown received new longterm contracts to support programs of the ~ a r s h a l lSpace Flight Center. The awards included prime contracts to support the Propulsion and Vehicle Engineering Laboratory and the Research Projects Laboratory at the center, as well as subcontracts to support the Test Laboratory and the Quality and Reliabi lity Assurance Laboratory. These contracts represent potential sales of more than $100 million for Brown over a five-year period. Since these are awardfee type contracts, under which the company's fee is governed by the quality of i t s performance, Brown has the opportunity to real ire greater profits than it did from former mission support agreernenk the study of materials used in the v e hicles. Brown also contributed to such advanced projectsas preliminary studies for manned orbital vehicles and tightweight surface vehicles for lunar exploration. As the prime contractar to the Propulsion and Vehicle Engineering Laboratory, Brown provides technical support to MSFC's mission to develop Saturn space boosters far America's moon program. The company has technical and professional personnel of almost every scientific discipline assigned to this task. Their work includes such activities as the analysis of the Saturn vehicle's structure, engines, and propulsion systems; the integration of major systems that are necessary to form the complete vehicle; the evaluation of r e lated ground support equipment; and MSFC's Quality and Reliability Laboratory included the development and aperatian of an automated information storage and retrieval system which provides reliability data on parts and materials used in the Apollo space program. Known as the Apolla Parts Information Center (APIC), this system is ab te to automaticajly answer the queries of ather NASA centers and industries associated with the space program. The highly sophisticated system is particularly advantageous to today's widespread, but fast moving,space program, because it accepts inquiries 24 Brown's significant contAbutions to 7% ddatrnifle the mdian of fuaf lh the h k s is beyand #e MI & ih'e esifh's ~ a v Brow? deveIcp? a unique methad Tor d f m v ethg thts condr D ~ by I kmng me fluH float En amtkr. HHeae, a Hue Ifqtrid, floafin in a red flrrfd, !s Wb~atedto s h o ~resmrJm w b t might ~e p m in the ,fuel tank a' 9 miffg kr#W whlcle. of a space v'ehi'efewhim It �hours a day and tranmiu or r-ives text?phot~gnph$,and drawtna;s over a world-wide network. In Suppart of the MSPC Test L h m bry, Brown test$ .components and subsystems far qaGe v&icles and related ground supp,rrt equipment by evaluatIng their r e d o n in hasrile mimmen&. Addithnallp, the ~ompanyde sign5 faciIitia for testi% en@& and bgaste35, and designs and buitds spe- cial fixtures that a r ~us& in w&- mental t@Tirlg. Brow<nYsrole in the space proairam at the Ma&all $pace Flight Cmtw also murrnpas pwjeas that lie beyond ,tudafi's Apnlb moon missfon. As the prime soure for m h n t d suppart ta MSFC's Research Projem Letboramry; the mmpat~yIs a prWia1 parkkipant' in scientific programs assocbtd with mads wrrt.irtut#g invstigatians o# the universe after he reachathe moan. a r c h and &velupment auppo& w a provided b r inettiat ,~idarrc~. ahd ~ m trd .equi~mmtfor a VTQL ~ v d d Wffand landinid 9ikmft- ltESEARCH ri The seIeEtSan of @to q p oj NASA's R e m d h~ i e & tabo-q at -the NASA / b lZ a r W Spwe FIEght Center IhWCl ef1ecYs s ~ !y an oar increased c q ~ b i f i t 3 e li'n ~ this parea tn additinn to p ~ m g . a s i s I s ~ ~ e potted the A m y Materiel ~pmrrtmd's to this MSN= function, Brown's BEN i b % Praft. Office In the deielop- s d ~aft3tb.Biti~ were also d h c t d meht of Pcmerid5 anti-missile missile md a c c o m p l i € a t of sdew system through the perforfia'nce of en- tifir: sftrdles for other NASA o t g a b #neering, Wi, and ahalpis t a 8 b tionst the A m y , and Navy, as we11 as Under a cunmct from the Army Mi+ #he dwekymM of new products and sile Cammand, %a rompmy dweloped tedtnolqies for the company, a guidance and control spterrt for a with MSFC*$ REnew anti-tank . n b s i l ~In a d j t i ~ n ,re- Under the con= The company made signif iamt cotrtributlona in 1965 ta the Atmy's dwelapc merit of m i a l e and aircraftpa -1 t as an automat& zystern far stouing.andre trhvlng m$ineering data. Bro,wn s ~ * �Exampfa af muM-layer cfrcuR baa& and nnfed w&Rn develcrw and manuktured gy Bawn ~ngkseringand its ruhsidia@, Elecfro-Mechanisms, Cktu/try shown above is part of Wernefw egujpment used fo trmsmff vltal dab back to Earth from Saturn space vehlclm. �of flexible printed cabling a d multilayer circuit baa& was acquired as a subsidiary. A joint venture was effected with another company specializing k data acquisiaon systems, A new division, to be housed in a modern plant a€ Lewisburg, Tennessee, was created to continue the company" telemetry and instrumentafion operations. Advances were made in the field of micmcircuitry, new products were introduced, and other products were improved to take advantage of new market putentials and advancing techndogins. last, Firrther, Ef the computer should FaiI completely, the DCE's control panel allows vehicle checkout te be performed manually, avoiding the enormous ms,t af an aborted mIssian. The DCE is capable of receiving and processing command signals controlling up ta 21116 discrete function's within the vehicle. To accomplish this gigantic feat requires approximately 13,000 electronic module assernbtia wwithin each of the nine DCE systems currently being hui lt. The DDAS receives data transm ftted from the Saturn vehicle, decodes it, and presenb it for evaluation. The cornplexity of this equipment is indicated by the fact that 103 major racks of equipment Brawn continues to be the largest supplier of telemetry and i nstrumen-tatian equipment for the Saturn program, not only to NASA, but to many of NASA's prime contracQrs as well. Thew incl ude No~th American Aviation, Boeing, Dauglas, IBM, and General dectric. Plans are underway to add a line of industrial and commercial talemetry equipment fe the aerospace and defense units Brawn builds. Telemetry equipment has appIicatians fur remote monitoring in process cuntrol, biomedicine, petrateurn, and chemical in- dustries. Perhaps the mest significant contributions to Brown's diversification in elmtronics are the subsidiary acquisltians are required. and facility expansions that took place Other contracts awarded to Brown in 1965, Engineering during 1965 include one The acquisition of Flectro-Meckanwith the Air Farce's Rome Air Develop- isms, Int., finalized in 1965, has pravan ment Center and one with NASA's to be an extremely good investment, Langtey Research Center. The Rome This young, dynamic, and profitable contract is Brown's first major research subsidiary has increased its grass sales contract with the Air Force and calls from $500,000 in 1964 to almost $3 The DCE, designed by Brown under an for the company to investigate the fun- million in 1965. Electro-Mechanisms earlier contract, incorporates a high de- damental limitations of negativeresis- has facilities in Methuen, Massachusetts, gree of reliability through the use af tance semi-conductor devices used in and Nashua, New Hampshire, and is triple-redundant voter circuitry. This communications systems, The Langley currently seeking new plant locations feature allow$ the DCE to continue to contract fe for design, development, far future expansion of its printed cirfunction in the event one of fie signals and manufacture of an aircraft-tu-air- cuit cabling and multi-layer circuit from the Saturn Ground Computer is craft ranging and altimeter system. boards. To link Saturn Y space vehicles to au- tomated checkout equipment, Brawn is building discrete control equipment (DCE) and a digltal data acquisition system (DDASI for checkout and monitoring functions before and during the launching of these vehicles. The relationship of this equipment to NAmSA's Apollo program (moon mission) is depicted on the facing page. ContmI Ewlpwnt IDCEI systems are shown herre w parts of the Saturn Ground Computer System, Also shown Is IP Digital Data Aqdsitlotr System (DDASI, being brrllt by Brawn under mntract b General Electric. A fonctlanal d@scr/ptEonof thesystms follews: (!) W L X E is kccased at the Launcher Umbi11wlTower (&LET) fu aubmat!calfy translate cwmnands from the Bturn Gmnd Corn utet Into discrete control tunet~ons !or veRicie d m m t (automstic made). The- WE may also be opemted /n ft8 manud mode $0 rnwlrrally r'nftlateconiF'o1 funcbans through a control pane) located dthes on the DCE itself (local mandmadel or UP bc 7 miles away f r e p t s manual mdBI. 121 The DDAS recervas stma& Pam the Saturn vehIek Which indicate the varl~useven& &king p/ace In the vehfcie duflng performance of uehTcYe checkout. T b m signals are tmns!atd fnta d&ifat language by the DbAS and relayed to the Saturn Ground Cornpuh far evdmtid~,The DDAS mmtlnues to mcelve data after rehkk launch through t e l m wur'p~~~ent. ~ 133 The Two of h w d s DIscreie Saturn G m n d Compuw at f h LUT is canneefed b ern )dentical eompuhr at the Launch Cantfol Center (LCCl so that the en the operation of the LW mmpmr /$ du Itcaw In the LCC carnplmv 141 A second D& is located sf the LCC and ls connecW to the LCC m p o f e r In the same wa that the flat DCE E s cannested to the computer, Thus, since hofh DCPs are funMming In fha same manner and receiviq idwEia1 inputs, the outputs are Ilkewlse ident/cat, 151 An hd!Wor panel Is ccmneeted to tha output ind df the secorPd DCE In the same way that the W r n vehtcle is connmed to the first WE. Slncs the outputs of bofh EE's are Idenikal, the Indicator panel can be made to Ino'rcate an or all of fie contra/ fmctim baing a p p d t o ~ l vee h/&. Thus, pednrmance df th& entire grdund checkout flocedure, fakM place at the LUT, ten be m i t o & af the l&,before and after /aurrch. In add~Yion, all nr any pari pf the LX checkout procedure can bs mtr&fI& manualy through tha first DCE3 &of panel. ���B R W N ENGINEERING COMPANY, IVC., AND SUBSIDlARlES Y e m ended Bembm-31, I=, a d kmhr *I, 19# -I965 . ,\ lS4 I ! . I ~e~era~'and:ad&ni~trafjve expense : . . . . . . . INCOME FROM QPERATIUNS Other deductions; tnt~restmpmw . . . 0th expmm - net . . . . . . . . . . . INCUMZ BEFORE TAXES ON INCOME T a a on inmme - Note C: Federalincgmehat~s . . . . . . . . . . . . State i n m e t a x e . . . . . . . . . . . . . TOTAL T A X B QN INCOME NET INCOME Add retained earning at bqginming wf year . . . . . . . 2,003,337 $ 3i137,315 W u a ~ $ 5 1 7dividends paid - $.XI a ahare in 1965, and 1964 146,352 RETAtNEDEARNING5ATEND OF YEAR $2,991,263 Deprecktisn and a m r t i z a i o n inciwded above: Year ended Dwernbw 31,1965 - $938,m. Year ended Chcmbw 31,1964- $ W , J 1 5 . !3emates to .amdidaid financial state man^. . . . . . . . . Warking capital at begrnntngof yeat Addilms: Cash fun& p W d & by operatiatd~: Werinramc . . . . . . . . . . . . . ~ @;$ . Prmkion for depredaQanand amortleation of pmpmty, plant,equiprnmf, ad kmhald irnprravemenQ . . . . . . . . . . . Amortkatian ~f rnimltmenus quiprnmt a d y he* ~;ro.n-& expenses I n m in~Iang-mrm debt . . . . . . . . . . 5ak ef Eammm 5tuc.lc under employee slack aptiopla m,$% . . . . . . . Oducticrns: Cash $ivkhn& paid . . . . . . . . . . . Net additions t . property, ~ plant, equipment, and teamhold impravmen& M d I n r m c in maher mn-currant Working capital at end of year . . . . . . . . . . . .. . 4 m* . %' -&## - ? > ,' - �����A joint venture with Trans-Data, hcWd Another addition occurring in 1965 may scrgn r ~ ~ uinl tB m d s acqukition was tha &tabfishhentof n micrclcfrcuit of this Huntsvj IIe-based company. laboratory in the WunBville facility: Trans-Data, Inz., has qecialized =pa- Mlc~o:oelectronicpackaging tech iques Mities in the dpign and development now being developed will be used to af ground-based data acqsluhitlan sys- develop a transmitter that will send up tem. to 50 channels of data, The unique Lewisburg, lenn~ssae,b the site of asp%!& of this trahsmftter is that jjt will anather expandon of Brawn" elmren- be only one inch In diameter by five ia capabilities A new manufacturtng irr&es long, and will transmit data from plant b being built on a 30-aae sit& in with in the shaft of a rotating turbine. kwi3burg's new i n d ~ t r i a lpark. The plant will allow Brown to maintain its position as a principal supplier of te- New electronic products develaped in lemetry and Instrumentation equipment 1964 by Brown include a "sslder-lwb far the space program and will m m Ing" machine for applying proterrlve the additional floor space requirements solder a a t h g s to printed-drcult boards Fdr the M r e emergence of the com- for wttmeIy high-reliability applimtians. This machine represents s siftpany i n t ~cgntmercial markets. nificmt advance in the state of the art, hwaus i-t cah decr&a~eproduction time ahd costs o w previous methods. Weml ac-w items have been developed far the Brow- clwed-circuit tele-vEs4an canara. These Include an optleal pan/tilt/zoorn .device which enables an operator to vary the camera's field of view f m a remote lmation whik the camera itself remains stationary. The camem has also undergone tedesi~n.As a result, it can be bui tt more ecanomfally ahd offers improved reliability, performance, maintainability, and flexibility. Additianally, Brown camera can be modified so that it wjll be sensitive to infrared light far detedtion of hydrogen flm. It is expected that this modification will find the a/seaming igmlsnt e m f l y lnstaited P" "iIte" facjtlty t~ mwrt pewrfitm m t e r s &ecfly I n b m a W I e 'Y,pe O a Drqwn% Wuntw enk& md mlerufilmrecords. This &v!ce can five different type fonts at the rate 6f 2;aod &MWS per SWM, �widespread applications in both government and commercial areas. Strobe lighting is also being used in conjunction w i t h the camera, lending t o a variety of "exploring" applications: inspection of caves, drilled holes, and buried pipe lines. ing used in two major airborne navigation projects. Brown's BECON connector line has n o w been expanded t o 29 bas~ctypes, four of which were added in 1965. In addition, Brown makes 1 2 types of custom-designed BECON connectors for special applications. Another product improvement is the adaptation of the company's BECON printed-circuit connectors as microcircuit carriers. An outstanding feature of these connectors is that the microcircuits are held t o the carrier b y spring clips instead of solder, facilitating considerably the replacement of circuit elements. This approach is currently be- INFORMATION SCIENCES / Brown's capabilities in computer sciences increased significantly in 1965. A whollyo w n e d subsidiary, l n f o r m a t i o n Sciences, Inc., was established in Atlanta. A n I B M 360 computer and a Philco 6000 optical scanner were installed at the Huntsville facility, A centralized information-dissemination system was de- veloped for shipboard helicopter maintenance. A n d several extremely complex computer simulation models were developed for the U.S. Army and NASA, including an analysis of the saturation probability of a defensive missile syst e m and a detailed analysis o f a wheeled vehicle operating over the surface of the moon. Information Sciences, Inc., Brown's new subsidiary, is presently providing data processing services, automated engineering and management services, and technical publications services t o aircraft, aerospace, defense, and commercial customers, including many small Disc storage unit of IBM 360, Model 40, computer, recently installed at Brown's computer facility. This disc system offers several operating advantages over magnetic tape. �businesses throughout the Southeast. Since this subsidiary was established in Atlanta, Georgia, only last July, employment has more than doubled and branch offices have been established in four Southeastern cities: Huntsville, Birmingham, and Montgomery, Alabama, and Merritt Island, Florida. In order to better serve this market, an IBM 360, Model 40, computer was installed. In support of i t s program to develop an automated engineering data system for the U. S. Army, Brown installed an advanced optical scanner that directly converts typed words and numerals to computer symbols and transcribes them on magnetic tape. This sophisticated technique virtually eliminates the time-consuming chore of keypunching information before placing i t on tape. mission and closed-circuit television to bring the needed information to the particular shop. Brown also developed a method for the automatic writing of military speUnder a contract with the U. S. Army, cifications by computer, and a comBrown designed and developed an in- puter simulation program for evaluating formation-dissemination system for use the mobility performance of wheeled in a floating aircraft maintenance fa- vehicles on the moon's surface is becility for offshore maintenance and re- ing investigated by Brown for NASA. pair of helicopters. This system allows any of the various shops aboard ship to STRUCTURAL AND MECHANICAL SYSquickly obtain maintenance and repair TEMS / Over the years Brown has esinformation from a central data storage tablished and expanded specialized unit. Brown's system, which i s micro- fabrication and testing capabilities to film oriented, utilizes facsimile trans- support the company's intimate role Test fixture in Brown Engineering's Test Laboratory for dynamic testing of rocket engine gimbals. Gimbal under test is for engine used in third stage of Saturn V space vehicle. ��I ' 1 , 1 services being provided t o NASA, the U. S. Navy, industry, municipal governments, and private citizens. to partrcipate In the manufacture and testrng of grant arms rt desrgned t o support service Irnes gorng from ground equrpment t o the Saturn vehicles. Brown also evaluated the relrability of electrical, mechanrcal, hydraulic, and pneumatic components for the Saturn ground support equrpment, and the company burlt and ~nstalledelectronrc instrumentatron equrpment for handlrng hazardous lrqurd propellants used In space vehicles. Reed-Mullrns and Associates, Brown's architects-engrneers, desrgned a new Federal Offrce Burldrng and Court House In Tuscaloosa, Alabama. The modern three-story structure wrll feature a penthouse and wrll contain approxrl~lately63,000 square feet of floor space ARCHITECTURE AND FACILITIES ENGINEERING / During 1965, Brown continued t o expand its capabilities in architecture and facilities engineering, with Brown's Facilrties Engrneerrng Department performed work on a turbrne engrne test facilrty for the U. S. Navy, completed design and construction Herbert Johnson Towers, a recently completed apartment building for the aged, was designed by Brown's Reed-Mullins and Associates. This eight-story structure is conveniently located near several of Huntsville's shopping centers and incorporates many unrque convenrences, particularly suitable to its residents. drawings for Brown's new test facility, and desrgned a thermal rnsulation test facilrty and a mobrle acoustrc research laboratory for NASA's George C. Marshall Space Flrght Center (MSFC). The m o b ~ l eacoustrc research laboratory 1s an easrly-movable acoustic test facility for exposlng large test specrmens, werghrng up to 30,000 pounds, to the tremendous nolse levels produced by a Saturn V booster whrle ~t is b e ~ n gtest fired Brown helped develop comprehenslve master plans for MSFC facrlrtres rn Huntsv~lle,Alabama, and Michoud, Loursrana, covering such Items as rarlI oads, utr lrtres, roadways, drarnage, securrty, and crvrl defense. �THE FUTURE upon the recommendation of the board of directors, a Curparate Development and Planning Committee was organized to examine the future p a l s of the company and to apply its talents te the solution of problems vital ta Bruwn's continued growth and development, This committee has developed an aggrasive plan for growth that includes sales and profit goals and acquisition plans for Brown. Further, a Future Programs Office was established to enhance the company's opportunities for participating in new government and industry research and development programs and to broaden Brawn's participation in existing programs. In the future, Brown expects to cornmand a major rota in significant new developments on earth, as well as outer spare. Aggresive goals for sales, earnings, market expansion, and technaIogical advances are a part ad this course. Such goals are considered realistic, be cause Brown's interests over the next decade parallel the demands and problems America's growing population and prusperity are expected to creak. Brown believes that it is In a strong position to make important contributions to future space developments, because of the amciation the company has with today's moon program in its work for NASA The company looks forward to increased partidpation in missile devafupment programsfor the Army, a5 well as the research and develupment t a s k sf other branches of the military, Brown also expects to be one of the companies that will contribute solu- tions to America's mass transporntian problems an earth. It believes that the same technologies that will carry man from earth to h e maan can be applied to get man from his home to his office. The company's expanding electronim capabilities promise to give Brown a significant share of the rapid growth market far large special-purpose systems, special packaging devices, microcircuitry, and closed-circuit television, Brown expects to be a prominent competitor far the virtually unlimited information retrieval and computer m i c e market. Through a subsidiary, the company has already made a position fur itself in this commercial field. As department stores, warehouses, utilities, and others turn to computers to serve their gruwlng l i n e af customers, Brown's future is expected to spiral upward in this a m . Laset. research, carried on by the company for several year% is expected to bring about significant applications for this exotic light source in medicine and industry. Spccialized design, engineering, manufacturing, and testing capabilitis within the same complex has put Brown irl an excellent position to participate in the development of major systems. The company's corrtribution~in the farm of modern hospitals, libraries, industrial plants, and other public buildings are expected to be recognized as enginears and architects are chosen for the future development of the nation's communities. The company looks to this future with optimism and enthusiasm. �BROUln E161nEERllRG FACILITIES ELECTRO-MECHANISMS, INC. ACi . - ..ISLAND, FLA. �OFFICERS1 From the top, Milton K. Cummings, President Joseph C. Moquin, Executive Vice President Robert B. Anderson, Senior Vice President WiIliam A. Giardini, Vice President Raymond C. Watson, Jt.,Vice President lack W. Hendrix, Vice President of Administration William 1. Vernon, Secretary and Treasurer DIRECTORS Milton K. Cummings, Chairman Robert B. Anderson William A. Giardini Elliot Coldstein Thomas D. johnson M. H. Lanier, jr. H. E. Monroe JosephC. Moquin Sidney IG Tally Kenneth I. Thornhill William 1. Vernon D~im, copy, art, photagraphy, 24 and printing by I s m n En~lneeringCompany �� Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000067 Title A name given to the resource "Annual Report of Brown Engineering Company, Inc. For the Year Ended December 31, 1965." Creator An entity primarily responsible for making the resource Brown Engineering Co. Date A point or period of time associated with an event in the lifecycle of the resource 1966-02-01 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn Project (U.S.) Aerospace industries--United States--Periodicals Brown Engineering Co. Type The nature or genre of the resource Annual reports Text Source A related resource from which the described resource is derived Saturn V Collection University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000051_000074 https://digitalprojects.uah.edu/files/original/193/13796/Defense_Billboard_126_001.pdf 74bb228e0d2922e0d99c80e6146f423e PDF Text Text B I L L B O A R D 126 See your voting officer American Forces Information Service • Department of Defense 601N. FairfaxStreet Suite 312.• Alexandria. VA 22314-2007 • (703) 42*0283, DSN 328-0283 � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Defense Billboard Posters Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context Defense_Billboard_126 Title A name given to the resource "Any way you cut it...you hold the winning hand (See your voting officer)" Alternative Title An alternative name for the resource. The distinction between titles and alternative titles is application-specific. D2.9:D36/2/No.126 Description An account of the resource Military uniform holding cards with words vote and register Creator An entity primarily responsible for making the resource Department of Defense Date A point or period of time associated with an event in the lifecycle of the resource 1998-07-23 Temporal Coverage Temporal characteristics of the resource. 1990-1999 Subject The topic of the resource Department of Defense poster United States--Department of Defense Voter registration Playing cards Puns Type The nature or genre of the resource Posters Still Image Source A related resource from which the described resource is derived The University of Alabama in Huntsville M. Louis Salmon Library Defense Billboards Posters Case 1, Drawer 1 Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource Defense Billboards https://digitalprojects.uah.edu/files/original/20/2306/spc_stnv_000078.pdf caeccc01f22dd0f69d6603d64ccefc37 Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000078 Title A name given to the resource "Apollo - LEM Docking Drogue Assembly Static Structural Test." Alternative Title An alternative name for the resource. The distinction between titles and alternative titles is application-specific. SID 67-318 TR 332015A CTR 02332015 Description An account of the resource This document contains the tests and test results from structural tests performed on the Apollo LEM docking drogue assembly between January 11, 1967 and February 15, 1967. The document contains various graphs, diagrams, and images pertaining to the tests. Creator An entity primarily responsible for making the resource North American Aviation, Incorporated. Space and Information Systems Division. Subject The topic of the resource Apollo lunar experiment module Loads (Mechanics) Project Apollo (U.S.) Saturn Project (U.S.) Spacecraft docking Static tests Towed bodies Source A related resource from which the described resource is derived Saturn V Collection Box 21, Folder 27 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000075_000118 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. http://libarchstor.uah.edu:8081/repositories/2/archival_objects/17654 Date A point or period of time associated with an event in the lifecycle of the resource 1967-04 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Type The nature or genre of the resource Reports Still Image Text https://digitalprojects.uah.edu/files/original/20/10411/Skywritermay2369_121310160336.pdf c9b809c5bff5f4dd2408b92c8983205c Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context Skywritermay2369_121310160336.pdf spc_stnv_000817 Title A name given to the resource "Apollo 10 crew ready for return from space." Description An account of the resource News article detailing the Apollo 10 crew's preparations to return to Earth from lunar orbit. Creator An entity primarily responsible for making the resource Elliott, J. S. North American Rockwell Corporation Date A point or period of time associated with an event in the lifecycle of the resource 1969-05-23 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn project Periodicals Aerospace industries Type The nature or genre of the resource Text News Articles Source A related resource from which the described resource is derived Saturn V Collection Box 31, Folder 37 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000800_000824 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. http://libarchstor.uah.edu:8081/repositories/2/archival_objects/18120 https://digitalprojects.uah.edu/files/original/20/10412/Skywritermay969_121310160912.pdf 6068df58b824f3de5c07c85af6c19d9a Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context Skywritermay969_121310160912.pdf spc_stnv_000818 Title A name given to the resource "Apollo 10 in spotlight as CDDT is completed." Description An account of the resource News article detailing the attention Apollo 10 is getting after its successful countdown demonstration test (CDDT). Creator An entity primarily responsible for making the resource Elliott, J. S. North American Rockwell Corporation Date A point or period of time associated with an event in the lifecycle of the resource 1969-05-09 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn project Periodicals Aerospace industries Type The nature or genre of the resource Text News Articles Source A related resource from which the described resource is derived Saturn V Collection Box 31, Folder 31 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000800_000824 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. http://libarchstor.uah.edu:8081/repositories/2/archival_objects/18114